公开(公告)号：US09551552B2

公开(公告)日：2017-01-24

申请号：US13839637

申请日：2013-03-15

Applicant: Orbital ATK, Inc.

Inventor： James Kolanek ,  Behshad Baseghi ,  David Sharpin ,  Anthony Visco ,  Falin Shieh

IPC: F41G7/34 ,  F42B10/66 ,  F42B15/01 ,  F41G7/00 ,  F41H11/02 ,  F41G7/30 ,  F42B15/10 ,  G05D1/08 ,  F42B10/00 ,  F42B15/00

CPC classification number: F41G7/34 ,  F41G7/007 ,  F41G7/303 ,  F41H11/02 ,  F42B10/66 ,  F42B15/01 ,  F42B15/105 ,  G05D1/0808

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

Abstract translation: 实施例包括用于空中平台的主动保护系统和方法。 车载系统包括雷达模块，检测空中平台威胁范围内的飞行器，并确定是否有任何空中飞行器是空中威胁。 车载系统还确定到空中威胁的拦截矢量，将拦截矢量传达到弹出车辆，并使弹出车辆从空中平台弹出以拦截空中威胁。 弹出车辆包括对准推进器，以使喷射车辆的纵向轴线旋转以与拦截矢量基本对准，火箭发动机沿着拦截矢量加速喷射车辆，使推进器沿大致垂直于拦截矢量的方向转向喷射车辆 拦截矢量和姿态控制推进器来调整喷射车的姿态。

公开(公告)号：US08637798B2

公开(公告)日：2014-01-28

申请号：US13316553

申请日：2011-12-11

Applicant: Jahangir S. Rastegar

Inventor： Jahangir S. Rastegar

IPC: F41G7/00 ,  F42B15/01 ,  F42B15/00

CPC classification number: F41G7/34 ,  F41G7/346

Abstract: A method for determining a position of a device in a reference coordinate system. The method including: receiving, at the device, less than all of GPS signals necessary to determine the position of the device in the reference coordinate system; transmitting a signal from aν illuminating source defined in the reference coordinate system; receiving the signal at a cavity waveguide disposed on the device; and determining the position of the device in the reference coordinate system based on the GPS signals and the signal received in the cavity waveguide. The signal received in the cavity waveguide can also be used to confirm a position determined by the GPS signals.

Abstract translation: 一种用于确定参考坐标系中的设备的位置的方法。 该方法包括：在设备处接收少于确定参考坐标系中设备的位置所需的全部GPS信号; 从参考坐标系中定义的anu照明源发送信号; 在设置在所述装置上的腔波导处接收所述信号; 并且基于GPS信号和在腔波导中接收的信号来确定设备在参考坐标系中的位置。 在腔波导中接收的信号也可以用于确认由GPS信号确定的位置。

公开(公告)号：US08265817B2

公开(公告)日：2012-09-11

申请号：US12216758

申请日：2008-07-10

Applicant: Gene D. Tener ,  Andrew H. Hawkins ,  Mark A. Bovankovich ,  Louis N. Glaros

Inventor： Gene D. Tener ,  Andrew H. Hawkins ,  Mark A. Bovankovich ,  Louis N. Glaros

IPC: G01C22/00

CPC classification number: G01C21/005 ,  F41G7/34 ,  G01S5/163 ,  G01S13/876 ,  G01S17/875 ,  G05D1/10 ,  G06T7/75 ,  G06T2207/10032 ,  G06T2207/30252

Abstract: The present invention relates to a system and method for determining vehicle attitude and position from image data detected by sensors in a vehicle. The invention uses calculated differences between the locations of selected features in an image plane and the location of corresponding features in a terrain map to determine the attitude of the vehicle carrying the sensors with respect to a ground frame of reference.

Abstract translation: 本发明涉及一种用于根据车辆中的传感器检测到的图像数据来确定车辆姿态和位置的系统和方法。 本发明使用图像平面中所选特征的位置与地形图中对应特征的位置之间的计算差异来确定携带传感器相对于地面参照系的车辆的姿态。

公开(公告)号：US08222582B1

公开(公告)日：2012-07-17

申请号：US12584591

申请日：2009-08-31

Applicant: Mark J. Anderson

Inventor： Mark J. Anderson

IPC: G01C21/02 ,  G01C21/20 ,  F42B15/01 ,  G01C21/00 ,  F42B15/00

CPC classification number: G01C21/025 ,  F41G7/34 ,  F42B15/01 ,  G01J3/28 ,  G01S3/7867

Abstract: A method is provided for characterizing luminous celestial objects (e.g., stars) in celestial navigation of a missile system. The method includes segmenting, assigning, measuring, computing, ratioing, producing, scaling, and determining operations. Segmenting includes subdividing wavelength range into discrete contiguous bins. Assigning arranges each bin into a plurality of color bands. Establishing sets a transmissivity to each bin of each color band. Computing calculates broad-based fluxes for a reference value as a reference flux. Ratioing computes a ratio between the target flux to the library flux as a color scale for each band. Squaring determines the library flux for each band as a library flux squared. Producing sums a spectral scale over the color bands, a second multiplication of the color scale and the library flux squared as a first sum product, and sums over all the bands the library flux squared as a second sum product and dividing the sum products. Scaling factors each measured intensity of the measured intensities as a scaled intensity by multiplying each target intensity by the spectral scale for each bin. Determining sums a scaled broad-band flux for each band over the bins, a third multiplication of the transmissivity and the scaled intensity.

Abstract translation: 提供了一种用于表征导弹系统的天体导航中的发光天体（例如，星星）的方法。 该方法包括分割，分配，测量，计算，比较，生成，缩放和确定操作。 分段包括将波长范围细分为离散连续的分区。 分配将每个仓排列成多个色带。 建立设置每个色带的每个仓的透射率。 计算计算基准值的基准通量作为参考通量。 比率计算目标通量与库通量之间的比值，作为每个波段的色标。 平方确定每个频带的库通量作为库通量平方。 产生总和在色带上的光谱标度，颜色标度和库磁通量平方的第二次乘积作为第一和积，并将库磁通量平方的所有频带求和并作为第二和积并且求和积。 通过将每个目标强度乘以每个分区的光谱标度，将每个测量的强度的强度作为缩放强度进行比例。 确定对于箱上每个频带的缩放宽带通量的总和，透射率和缩放强度的第三乘法。

公开(公告)号：US07425918B2

公开(公告)日：2008-09-16

申请号：US11196695

申请日：2005-08-03

Applicant: Jahangir S. Rastegar ,  Carlos M. Pereira

Inventor： Jahangir S. Rastegar ,  Carlos M. Pereira

IPC: G01S7/40 ,  F41G7/00

CPC classification number: F41G7/001 ,  F41G7/34 ,  G01S5/0247 ,  G01S5/14 ,  G01S7/024

Abstract: Methods are provided where: a signal is transmitted from an illuminating source and received cavity waveguides disposed on an object; a position and/or orientation of the object is determined based on the signal received in the waveguides; and data representing the determined position and/or orientation is transmitted to a remote location or generated for use in the object. The illuminating source can also be moved to indicate a change in a predetermined trajectory or target position where a new position and/or orientation of the object is determined based on the signal received in the waveguides and the object is controlled to change the predetermined trajectory or target position to the indicated new predetermined trajectory or new target position. A change can also be detected in the predetermined trajectory or target position and the object controlled to correct the change.

Abstract translation: 提供了一种方法，其中：信号从照明源传送并且接收设置在物体上的腔波导; 基于在波导中接收的信号确定对象的位置和/或取向; 并且表示所确定的位置和/或取向的数据被发送到远程位置或者被生成用于该对象。 照明源还可以被移动以指示基于在波导中接收的信号来确定对象的新位置和/或取向的预定轨迹或目标位置的变化，并且对象被控制以改变预定轨迹，或者 目标位置到指示的新的预定轨迹或新的目标位置。 也可以在预定轨迹或目标位置中检测到变化，并且控制对象以校正变化。

公开(公告)号：US06460801B1

公开(公告)日：2002-10-08

申请号：US09862843

申请日：2001-05-23

Applicant: Joseph R. Mayersak

Inventor： Joseph R. Mayersak

IPC: B64C1514

CPC classification number: F42B10/663 ,  F41G7/007 ,  F41G7/34 ,  F42C19/00

Abstract: A jet bomb guidance system in which bi-directional nozzles are fired in a manner to produce force state changes resulting in improved level of control, greater force compatibility and greater efficiency in propellant fuel usage. The system includes four bi-directional nozzles spaced at 90 degree internals in which at least four single nozzles are open at any given instant to maintain a substantially constant gas pressure. The system may be positioned at the nose portion, tail portion, or center of gravity of the bomb.

Abstract translation: 一种喷气弹导引系统，其中双向喷嘴以产生力状态变化的方式被发射，导致改进的控制水平，更大的力相容性和更高的推进剂燃料使用效率。 该系统包括间隔90度内部的四个双向喷嘴，其中至少四个单个喷嘴在任何给定时刻打开以保持基本恒定的气体压力。 该系统可以位于炸弹的鼻部，尾部或重心处。

公开(公告)号：US4111382A

公开(公告)日：1978-09-05

申请号：US586010

申请日：1966-10-10

Applicant: Charles W. Kissinger

Inventor： Charles W. Kissinger

IPC: F41G3/08 ,  F41G7/34 ,  F42B15/12

CPC classification number: F41G3/08 ,  F41G7/34

Abstract: A ballistic missile guidance apparatus for compensating the trajectory of aallistic missile just prior to thrust termination by comparing the nominal trajectory with the actual flight parameters encountered during the powered stage of the flight and introducing compensating corrections to provide for an accurate ballistic flight. The comparison is made by storing the nominal kinematic parameters and comparing thereto the actual flight parameters obtained from the inertial guidance system.

公开(公告)号：US4097007A

公开(公告)日：1978-06-27

申请号：US722837

申请日：1976-09-13

Applicant: James J. Fagan ,  William F. Otto ,  William B. McKnight

Inventor： James J. Fagan ,  William F. Otto ,  William B. McKnight

IPC: F41G7/30 ,  F41G7/34 ,  F42B15/00

CPC classification number: F41G7/30 ,  F41G7/34

Abstract: A missile guidance system in which a projectile or missile is fired toward predetermined target with the missile being tracked on its flight toward the target by radar, processing the radar information in a computer apparatus and finally computing a new trajectory from the missile to the target and transmitting correction signals to a correction device on the missile including thrusters on the missile to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile. This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time. Thisenables the missile to only contain radar reflecting means, and correction detection and control means on the missile rather than having gyro and other type devices on board the missile which take up a considerable amount of space and weight.

Abstract translation: 导弹引导系统，其中射弹或导弹向预定目标射击，导弹在其飞行中通过雷达朝向目标进行跟踪，在计算机装置中处理雷达信息，并最终计算从导弹到目标的新轨迹 并将校正信号发送到导弹上的校正装置，包括导弹上的推进器，使导弹的轨迹变为新计算的导弹轨迹。 该系统通过重新计算从导弹到预定目标的轨迹，并在每次进行适当的校正时，在飞行中纠正导弹的轨迹。 这使导弹只能包含雷达反射装置，以及导弹上的校正检测和控制手段，而不是在导弹上拥有陀螺仪和其他类型的装置，占用了相当多的空间和重量。

公开(公告)号：US3905563A

公开(公告)日：1975-09-16

申请号：US35438673

申请日：1973-04-25

Applicant: FUJI HEAVY IND LTD

Inventor： NAGOSHI SABURO

IPC: F41G7/22 ,  F41G7/34 ,  G05D1/12 ,  F42B15/02 ,  F41G7/00

CPC classification number: F41G7/22 ,  F41G7/224 ,  F41G7/34 ,  G05D1/12

Abstract: A system for controlling a missile motion in the homing mode comprises means for designating by an error signal a direction in which a missile is guided in the homing mode, and means for compounding with the error signal a predetermined biasing signal imparting acceleration in one or two dimensions normal to a direction of the missile derivation. The biasing signal causes shells from anti-aircraft guns and anti-missile missiles to increase the miss-distance to the missile, within the allowable maneuverability of the missile, whereby the missile evades defensive action and finally zeroes in on a target.

Abstract translation: 用于在归位模式中控制导弹运动的系统包括用于通过误差信号指定导弹在归位模式中被引导的方向的装置，以及用于与误差信号混合的预定偏置信号给予一个或两个加速度的装置 尺寸与导弹推导方向相符。 在弹道导弹的允许机动性范围内，偏置信号会导致高射炮和反导弹的炮弹增加与导弹的错过距离，导弹逃避防御作用，最终在目标上归零。

公开(公告)号：US3777665A

公开(公告)日：1973-12-11

申请号：US3777665D

申请日：1972-08-03

Applicant: GEN ELECTRIC

Inventor： ZIEMBA R

IPC: F41G7/30 ,  F41G7/34 ,  F42C13/00 ,  F42C13/04 ,  F42C17/04 ,  F42C11/00 ,  F42C15/04

CPC classification number: F42C13/00 ,  F41G7/30 ,  F41G7/34 ,  F42C13/047 ,  F42C17/04

Abstract: An electronic, digital, time fuze, has a time base which is introduced over a radar command link at a rate which is inversely proportional to the desired projectile flight time. A target following ranging device, such as a ranging laser, provides target range information to a pulsed radar transmitter. The range signal from the ranging device controls a variable pulse rate control unit which in turn adjusts the transmitter pulse rate to a value inversely proportional to the target range. The transmitter is fixed to the weapon system and radiates in the direction of the projectile flight path. Each projectile includes a fuze actuating circuit consisting of an antenna, an r.f. detector, a fixed-set counter and a firing circuit. At launch, the fuze actuating circuit within each projectile becomes actuated a short distance after departure from the gun muzzle. As the projectile travels towards its target it receives a series of r.f. pulses at a rate which will just fill the counter when the projectile is at the proper range. The counter within the fuze counts the pulses received during its flight to target. When the fixed-set number has been accumulated, the firing circuit detonates the payload.

Abstract translation: 电子数字时间引信具有以与所需的射弹飞行时间成反比的速度在雷达指令链路上引入的时基。 目标跟踪测距装置，例如测距激光器，将目标范围信息提供给脉冲雷达发射机。 来自测距装置的量程信号控制可变脉冲率控制单元，该可变脉冲率控制单元又将发射器脉冲速率调节到与目标范围成反比的值。 发射机固定在武器系统上，沿射弹飞行路径辐射。 每个抛射体包括一个引信致动电路，由一个天线，一个r.f. 检测器，固定计数器和点火电路。 在发射时，每个弹药中的引信致动电路在离开枪口后离开一小段距离。 随着射弹向目标的传播，它接收了一系列的r.f. 当弹丸处于适当的范围时，脉冲的速度将只会填满计数器。 引信中的计数器将飞行期间收到的脉冲计数为目标。 当固定号码已被累积时，点火电路引爆有效载荷。