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公开(公告)号：US09207051B2
公开(公告)日：2015-12-08
申请号：US14737556
申请日：2015-06-12
Inventor： Kenneth D. Cleveland , Amy Pietrzak , Adam G. Butland , James H. Steenson, Jr. , David J. Schorr , Joseph Borysthen-Tkacz
IPC: F42B10/20
Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.
Abstract translation: 公开了一种用于部署弹丸的收起的控制表面的装置。 用于展开弹丸的收纳的控制表面的装置包括第一和第二热气体发生器，第一和第二气体室，活塞楔，活塞和桶。 首先，第一热气体发生器将热气体浪涌排放到第一气室中。 响应于排放到第一气体发生器中的热气的浪涌，活塞楔移动至少一个控制表面以破坏覆盖射弹的环境密封。 在经过预定时间之后，第二热气发生器将热气流浪涌入第二气室。 热气的浪涌取代了活塞和桶，以完全展开控制面。
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公开(公告)号：US11815335B2
公开(公告)日：2023-11-14
申请号：US16467243
申请日：2016-12-15
Inventor： Joseph D. Vasile , David J. Schorr , James H. Steenson, Jr.
IPC: F41G7/22
CPC classification number: F41G7/226 , F41G7/2293
Abstract: Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.
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公开(公告)号：US11175115B2
公开(公告)日：2021-11-16
申请号：US16467357
申请日：2017-01-05
Inventor： David J. Schorr , Jason H. Batchelder , Jeremy B. Gibson , James H. Steenson, Jr. , Joseph D. Vasile
Abstract: Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.
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公开(公告)号：US20210116216A1
公开(公告)日：2021-04-22
申请号：US16604011
申请日：2017-04-10
Inventor： David J. Schorr , Jason H. Batchelder , Jeremy B. Gibson , James H. Steenson, Jr.
Abstract: [A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising: roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.
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公开(公告)号：US10371494B2
公开(公告)日：2019-08-06
申请号：US15357407
申请日：2016-11-21
Inventor： David J. Schorr , Matthew F. Damiano , James H. Steenson, Jr.
Abstract: Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.
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Patent Agency Ranking
公开(公告)号：US10055648B1
公开(公告)日：2018-08-21
申请号：US15130227
申请日：2016-04-15
Inventor： Will R. Grigsby , Eric Louchard , David J. Schorr , Mitchell J. Nord , Joseph McGaughey , Somit S. Mathur
CPC classification number: G06K9/00771 , G06K9/0063 , G06K9/6267 , G06K2209/21
Abstract: Techniques are provided for detection, classification and tracking of surface contacts based on multispectral image data from sensors on maritime assets. An example system may include an anomaly detection circuit configured to detect an object based on anomalies in the variance of pixels of water surface image data. The system may also include an object motion tracking circuit configured to analyze motion of the object relative to water surface waves. The analysis may compensate for motion of the asset and sensors. The system may further include an object classification circuit configured to classify the object as an object of interest, based on the analyzed motion of the object, and as a threat, further based on size estimation, edge detection, surface texture analysis, and volume analysis. The range from the asset to the object may be estimated based on the relation of the object to a detected or estimated horizon line.
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7.发明申请Method and System of Measurement of Mach and Dynamic Pressure Using Internal Sensors 有权使用内部传感器测量马赫和动态压力的方法和系统公开(公告)号：US20160041196A1
公开(公告)日：2016-02-11
申请号：US14818432
申请日：2015-08-05
Inventor： Robert D. Frey, JR. , David J. Schorr
IPC: G01P5/16
Abstract: A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.
Abstract translation: 一种用于计算空速和动态压力的系统包括位于系统体内的系统体，内部加速度计，位于系统体内的内部压力传感器，内部压力传感器不被气密地密封在系统主体内并且能够测量 环境大气的静压，以及接收内部加速度计的处理器和能够经由轴向加速度计算马赫数的内部压力传感器，并且能够经由马赫数计算动态压力和真实空速。
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公开(公告)号：US20210102790A1
公开(公告)日：2021-04-08
申请号：US16595609
申请日：2019-10-08
Inventor： David J. Schorr , Matthew F. Chrobak , Thomas T. Scarberry , Richie Spitsberg , Paul E. Turner
Abstract: A rocket in one example includes separate chambers for storing two thrust grains: an initial thrust grain and a boost thrust grain. The initial thrust grain is stored in a first chamber and the boost thrust grain is stored in a second chamber. The initial thrust grain is ignited separately from the boost thrust grain, such as in a two-stage process where the initial thrust grain is ignited before, or at the same time as, the boost thrust grain. The initial thrust grain has a large surface area (different burn pattern) relative to the boost thrust grain, which causes the initial thrust grain to have a shorter burn time than the boost thrust grain.
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公开(公告)号：US20200080819A1
公开(公告)日：2020-03-12
申请号：US16467243
申请日：2016-12-15
Inventor： Joseph D. Vasile , David J. Schorr , James H. Steenson, Jr.
IPC: F41G7/22
Abstract: Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.
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公开(公告)号：US09933449B2
公开(公告)日：2018-04-03
申请号：US14818432
申请日：2015-08-05
Inventor： Robert D. Frey, Jr. , David J. Schorr
Abstract: A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.
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