Radio Wave Patents (Class 244/3.19)
  • Patent number: 10725169
    Abstract: In some examples, a system is configured to mount on an ownship vehicle and includes a phased-array radar device configured to transmit radar signals and receive returned radar signals. In some examples, the system also includes a surveillance transponder configured to receive surveillance signals from another vehicle. In some examples, the system further includes processing circuitry configured to detect an object based on the returned radar signals and determine a position of the other vehicle and a velocity vector of the other vehicle based on the received surveillance signals. In some examples, the system includes common signal and data processing circuitry that processes both data from the phased-array radar device and data from the surveillance transponder.
    Type: Grant
    Filed: November 9, 2017
    Date of Patent: July 28, 2020
    Assignee: Honeywell International Inc.
    Inventors: Katherine Goossen, David C. Vacanti
  • Patent number: 10620321
    Abstract: Apparatus and methods determine the rotational position of a spinning object. A satellite positioning system can be used to determine the spatial position of an object, which in turn can be used to guide the object. However, when the object is spinning, such as an artillery shell, then the rotational orientation should be known in order to properly actuate the control surfaces, such as fins, which will also be spinning.
    Type: Grant
    Filed: August 28, 2017
    Date of Patent: April 14, 2020
    Assignee: Interstate Electronics Corporation
    Inventors: Steven B. Alexander, Richard Redhead
  • Patent number: 10551854
    Abstract: A method for detecting a target object includes: identifying a target object in a monitored region, and calculating first state information of the target object with respect to this detection apparatus; estimating second state information of the target object after a pre-set delay duration value according to the first state information; and performing a processing operation on the target object according to the estimated second state information. The present disclosure can quickly and accurately complete the tracking and state estimation of a target object, which adds new functions and satisfies automation and intelligence requirements of a user for object tracking and movement state estimation.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: February 4, 2020
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventors: Jidong Wei, Ren Lin, Shengyang Chen, Huasen Zhang, Jun Ren
  • Patent number: 10444341
    Abstract: A method and radar system and vehicle that tracks an object is disclosed. A source signal is transmitted into a volume that includes the object. A reflected signal is received from the volume in response to the source signal. The reflected signal includes a reflection of the source signal from the object. A range is determined for the object from the reflected signal. A ground signal is estimated at the determined range and an amount of the ground signal in the reflected signal is estimated. The object is selected for tracking based on the estimate of the amount of the ground signal in the reflection from the object.
    Type: Grant
    Filed: March 6, 2017
    Date of Patent: October 15, 2019
    Assignee: GM GLOBAL TECHNOLOGY OPERATIONS LLC
    Inventors: Igal Bilik, Shahar Villeval, Shmuel Nedjar, Alexander Pokrass
  • Patent number: 10114126
    Abstract: Technology for surveying sensor locations on a physical platform is described. An estimated baseline vector can be calculated between a temporary navigation sensor and each fixed navigation sensor in a group of fixed navigation sensors. The temporary navigation sensor can be temporarily placed on the physical platform. The fixed navigation sensors can be installed on the physical platform. A refined baseline vector between the temporary navigation sensor and each fixed navigation sensor can be successively calculated by fixing carrier phase integer ambiguities that are variables used in the estimation of the baseline vector. A final survey distance between the temporary navigation sensor and each of the fixed navigation sensors can be generated using the refined baseline vector.
    Type: Grant
    Filed: April 30, 2015
    Date of Patent: October 30, 2018
    Assignee: Raytheon Company
    Inventors: Shuwu Wu, Ji Li, Tyler Thomas, Howard E. Wan
  • Patent number: 9923615
    Abstract: Provided are a method and an apparatus for generating and transmitting feedback signals for a plurality of reference signals having different directionality, in a wireless communication system. A terminal may receive the plurality of reference signals having different directionality, and transmit, to a transmission end, a feedback signal including a beam index which indicates one of the plurality of reference signals.
    Type: Grant
    Filed: July 24, 2014
    Date of Patent: March 20, 2018
    Assignee: LG ELECTRONICS INC.
    Inventors: Ilmu Byun, Hyunsoo Ko, Kungmin Park, Heejeong Cho, Hyeyoung Choi
  • Patent number: 9739570
    Abstract: A gimbal-assisted continuous-wave (CW) Doppler radar detection system mountable to an unmanned aircraft system may be rotated in three degrees of freedom relative to the UAS to provide targeted multidirectional obstacle detection by transmitting CW signals throughout a field of view and analyzing reflected signals from obstacles within the field of view. The radar assembly may be articulated to provide track-ahead detection in anticipation of a heading or altitude change of the UAS, to center on a detected obstacle in order to classify or identify it more clearly. The radar assembly may be rotated below the UAS and its field of view changed to increase breadth and accuracy at a shorter effective range, in order to determine real-time altitude or terrain data while the UAS executes a landing.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: August 22, 2017
    Assignee: uAvionix Corporation
    Inventor: Paul Beard
  • Patent number: 9725157
    Abstract: A method and device for automatically comparing two flight trajectories for an aircraft includes a central processing unit having a first comparison element for automatically comparing lateral trajectories of the two flight trajectories, and a second comparison element for automatically comparing vertical trajectories of these two flight trajectories, these comparisons being carried out successively leg by leg of the flights, these comparisons being carried out as long as the respective successive legs are identical and at least for a predefined distance in the horizontal plane.
    Type: Grant
    Filed: April 28, 2015
    Date of Patent: August 8, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Nicolas Albert, Boris Kozlow
  • Patent number: 9709372
    Abstract: A semi-active RF proximity fuze for warhead detonation is provided where external RADAR is available to illuminate the target. The fuze incorporates multiple receiving antennas with digital phase detection processing to distinguish the angle from which the target returns are received and uses that information to determine the detonation timing for the warhead. Detonation timing can be improved by processing the rate of change of the angle-to-target or processing the range and Doppler information to compensate for target velocity and distance.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: July 18, 2017
    Assignee: Raytheon Company
    Inventor: Jeffrey C. Edwards
  • Patent number: 9647330
    Abstract: A radome tip assembly has high fracture toughness due to a tip and a bushing fastener that attaches the tip to a radome where both the tip and bushing fastener are constructed from a mixture of aluminum oxide ceramic material and reinforcing silicon-carbide crystal whiskers and the radome is constructed of an oxide ceramic matrix composite material.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: May 9, 2017
    Assignee: The Boeing Company
    Inventor: Robert A. DiChiara
  • Patent number: 9012823
    Abstract: A vehicle, such as a missile, is disclosed. The vehicle includes an optically transparent dome, a vehicle body, and a brazed joint directly coupling the dome to the vehicle body. The dome is formed of a Nanocomposite Optical Ceramic (NCOC) material comprising two or more different types of nanograins dispersed in one another. Each nanograin type has a coefficient of thermal expansion (CTE), and an aggregate CTE of the NCOC material is based on the CTE of each nanograin type.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: April 21, 2015
    Assignee: Raytheon Company
    Inventors: Wayne L. Sunne, Christopher E. Pentland, Christopher D. Marr
  • Patent number: 9006628
    Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.
    Type: Grant
    Filed: April 5, 2010
    Date of Patent: April 14, 2015
    Assignee: Lone Star IP Holdings, LP
    Inventors: Steven D. Roemerman, John P. Volpi
  • Patent number: 8927915
    Abstract: Apparatus and a method for intercepting a rocket body during boost phase. A sensor is arranged to detect thermal emission in a range that is characteristic of a firing rocket body. The image detected by the sensor is applied to an analog-to-digital converter for digitization and application to a computer that includes a routine for separating the modulated photon energy of the detected image from the substantially unmodulated photon energy that characterizes rocket body emissions. The unmodulated photon energy, signature of the rocket body, may be utilized by a fire control system for tracking, targeting and aiming munitions at the firing rocket body.
    Type: Grant
    Filed: June 22, 2012
    Date of Patent: January 6, 2015
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Frank O. Clark
  • Patent number: 8829401
    Abstract: A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: September 9, 2014
    Assignee: The Boeing Company
    Inventors: Kevin Lutke, Aaron J. Kutzmann
  • Patent number: 8816261
    Abstract: Control surfaces secured tangentially to a round projectile, such that the lift force generated by the control surfaces is generated through the projectiles centerline. This eliminates the need for an opposing fin to counter roll moment. Sizing the control surfaces to form an equilateral triangle gives each panel equal span, and enables the force generated by two panels to be equal and opposite to that of the opposing panel. The end effect is that each panel only has two active states (neutral and positive deflection). Thus, a solenoid and a return spring may be used to control the canards. Additionally, the control panels may fold along the surface of the projectile, which frees up internal volume and minimizes the length of the control section.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: August 26, 2014
    Assignee: Raytheon Company
    Inventors: Jesse H. Blake, Matthew G. Murphy
  • Patent number: 8735788
    Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.
    Type: Grant
    Filed: February 18, 2011
    Date of Patent: May 27, 2014
    Assignee: Raytheon Company
    Inventors: Kenneth G. Preston, Michael A. Leal, Rondell J. Wilson, Richard C. Hussey
  • Patent number: 8723091
    Abstract: A mount for a seeker head includes a plane spanned by a holder frame in which the pitch motion of the device containing at least one detector can be performed with respect to the missile structure and within the holder frame, at right angles to the plane spanned by the holder frame, a rotating mechanism for the rotational yaw motion of the device containing at least one detector is arranged about a rotation axis lying in the plane spanned by the holder frame. The pitch and yaw motion of the device is possible in a range of much more than+/?90°.
    Type: Grant
    Filed: March 29, 2012
    Date of Patent: May 13, 2014
    Assignee: LFK-Lenkflugkoerpersystem GmbH
    Inventors: Roderich Rueger, Juergen Zoz
  • Patent number: 8710411
    Abstract: A method and system for determining an optimal missile intercept approach direction to maximize the probability of association between a remote sensor designated object and a corresponding missile seeker-observed object. The method and system calculates a distance metric between a remote sensor designated object and the corresponding missile seeker-observed object, and calculates the probability that the remote sensor designated object and the corresponding missile seeker-observed object have a smaller distance metric between them than between the remote sensor designated object and any other missile seeker-observed object.
    Type: Grant
    Filed: September 29, 2010
    Date of Patent: April 29, 2014
    Assignee: Lockheed Martin Corporation
    Inventor: Ronald H. LaPat
  • Patent number: 8711035
    Abstract: Apparatus and methods determine the rotational position of a spinning object. A satellite positioning system can be used to determine the spatial position of an object, which in turn can be used to guide the object. However, when the object is spinning, such as an artillery shell, then the rotational orientation should be known in order to properly actuate the control surfaces, such as fins, which will also be spinning.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: April 29, 2014
    Assignee: Interstate Electronics Corporation
    Inventors: Steven B. Alexander, Richard Redhead
  • Patent number: 8698058
    Abstract: A ranging seeker apparatus includes an RF antenna and a bistatic ranging detector operatively connected with the RF antenna. The RF antenna and bistatic ranging detector are operative for detecting one or more guidance objects in a RF band and providing angle and range data to the missile. Also, a missile including a missile body, a missile propulsion system disposed in or on the missile body, and the ranging bistatic RF seeker disposed in or on the missile body.
    Type: Grant
    Filed: July 23, 2010
    Date of Patent: April 15, 2014
    Assignee: Lockheed Martin Corporation
    Inventor: Ronald H. LaPat
  • Patent number: 8664575
    Abstract: A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.
    Type: Grant
    Filed: August 16, 2007
    Date of Patent: March 4, 2014
    Assignee: Rafael Advanced Defense Systems Ltd.
    Inventors: Yariv Bril, Yakov Hetz, Oded Yehezkeli, Ehud Chishinsky
  • Patent number: 8637798
    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 a? 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.
    Type: Grant
    Filed: December 11, 2011
    Date of Patent: January 28, 2014
    Assignee: Omnitek Partners LLC
    Inventor: Jahangir S. Rastegar
  • Patent number: 8610041
    Abstract: A system for engaging hostile air or space threats with a defensive missile, where the defensive missile comprises an antenna for receiving global positioning system (GPS) signals. A global positioning system receiver is coupled to said antenna, for receiving global positioning system signals directly from global positioning system satellites and global positioning system signals reflected from the threat. A processing arrangement processes the direct and reflected global positioning system signals for determining the position and velocity of the threat. Vectoring controls are coupled to the processing arrangement, and are responsive to the location of the threat for directing the defensive missile toward the threat. In a particular embodiment, the antenna of the defensive missile is directionally controllable, and the defensive missile includes an antenna direction controller responsive to the processor for directing at least a beam of the antenna toward the threat.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: December 17, 2013
    Assignee: Lockheed Martin Corporation
    Inventor: Jonathan A. Boardman
  • Patent number: 8598501
    Abstract: A sensor system uses ground emitters to illuminate a projectile in flight with a polarized RF beam. By monitoring the polarization modulation of RF signals received from antenna elements mounted on the projectile, both angular orientation and angular rate signals can be derived and used in the inertial solution in place of the gyroscope. Depending on the spacing and positional accuracies of the RF ground emitters, position information of the projectile may also be derived, which eliminates the need for accelerometers. When RF signals of ground emitter/s are blocked from the guided projectile, the sensor deploys another plurality of RF antennas mounted on the projectile nose to determine position and velocity vectors and orientation of incoming targets.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: December 3, 2013
    Assignee: Northrop Grumman Guidance an Electronics Co., Inc.
    Inventors: A. Douglas Meyer, Mostafa A. Karam, Charles A. Lee, Charles H. Volk
  • Patent number: 8586901
    Abstract: Embodiments of a guidance section that compensates for boresight error (BSE) caused by effects of a composite radome. The guidance section includes a BSE compensation element to add high-pass filtered noise to compensated BSE data. The guidance section also includes and a Kalman filter to generate line-of-sight rate (LOSR) BSE noise from the compensated BSE data and the added high-pass filtered noise. In some embodiments, a method for generating a revised BSE correction matrix is provided. The revised BSE correction matrix may compensate for BSE caused by effects in the composite radome and may correct for relative target velocity error.
    Type: Grant
    Filed: August 26, 2010
    Date of Patent: November 19, 2013
    Assignee: Raytheon Company
    Inventor: Robert L. Kesselring
  • Patent number: 8581161
    Abstract: A molded dichroic mirror and a seeker comprising a molded dichroic mirror are provided. The dichroic mirror may be molded from polysiloxane or lithia potash borosilicate and may be coated to reflect an infrared signal and configured to transmit a radio frequency signal between 33 GHz and 37 GHz.
    Type: Grant
    Filed: October 1, 2010
    Date of Patent: November 12, 2013
    Assignee: Raytheon Company
    Inventors: Byron B. Taylor, W. Howard Poisl
  • Patent number: 8575527
    Abstract: A vehicle including electro-optic (EO) imaging has a vehicle body having an outer surface including a front portion and a side portion, wherein the side portion includes a plurality of portholes. A propulsion source is within the vehicle body for moving the vehicle. A fixed EO imaging system having a field-of-regard (FOR) includes a plurality of fixed EO imaging sub-systems arrayed within the vehicle body. The fixed EO imaging sub-systems each have a different field-of-view (FOV) for providing a portion of the FOR and include a camera affixed within the vehicle body and an optical window secured to one of the portholes for transmitting electromagnetic radiation received from one of the portions of the FOR to the camera, wherein the cameras each generate image data representing one of the portions of the FOR therefrom. A processor is coupled to receive the image data from the plurality of fixed EO imaging sub-systems for combining the image data to provide composite image data spanning the FOR.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: November 5, 2013
    Assignee: Lockheed Martin Corporation
    Inventor: James A. Fry
  • Patent number: 8569669
    Abstract: A SAR image recorded by a reconnaissance system is transferred as a reference edge image together with the data of the trajectory as a reference. The signal of the infrared seeker head of the missile is converted into a virtual SAR edge image and compared to the SAR reference image to calculate the precise position of the missile.
    Type: Grant
    Filed: March 23, 2011
    Date of Patent: October 29, 2013
    Assignee: LFK-Lenkflugkoerpersysteme GmbH
    Inventors: Michael Holicki, Nikolaus Schweyer, Juergen Zoz
  • Patent number: 8552350
    Abstract: The 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.
    Type: Grant
    Filed: January 15, 2012
    Date of Patent: October 8, 2013
    Assignee: Raytheon Company
    Inventors: Michael S. Bielas, Edward C. Schlatter, Andrew B. Facciano, Philip C. Theriault, James A. Ebel, Robert J. LaPorte
  • Patent number: 8471186
    Abstract: In a CLOS missile guidance system, target and missile tracking data e.g. video image data are acquired on a UAV and transmitted to the missile where they are processed to provide guidance control data to the missile. Alternatively the video image data may be transmitted to a command station where the guidance control data is generated and transmitted to the missile, preferably via the UAV.
    Type: Grant
    Filed: January 8, 2010
    Date of Patent: June 25, 2013
    Assignee: MBDA UK Limited
    Inventor: Graham Patrick Wallis
  • Patent number: 8461501
    Abstract: Embodiments of a guided munition are provided, as are embodiments of a method for equipping a guided munition with a self-deploying dome cover. In one embodiment, the guided munition includes a munition body, a seeker dome coupled to the munition body, and a self-deploying dome cover disposed over the seeker dome. The self-deploying dome cover is configured to deploy and expose the seeker dome during munition flight in response to aerodynamic forces acting on the self-deploying dome cover.
    Type: Grant
    Filed: November 2, 2010
    Date of Patent: June 11, 2013
    Assignee: Raytheon Company
    Inventors: Darin S. Williams, Nicholas B. Saccketti, David B. Hatfield, Alexandra L. Blake, Richard J. Wright, Lawrence A. Westhoven, Jr.
  • Patent number: 8445823
    Abstract: Embodiments of a guided munition system are provided, as are embodiments of a combustive dome cover and methods for equipping a guided munition with a combustive dome cover. In one embodiment, the guided munition system includes a guided munition, which has a munition body and a seeker dome coupled thereto, and a combustive dome cover disposed over the seeker dome. The combustive dome cover is configured to uncover the seeker dome at a predetermined time of deployment and to combust when so deployed to minimize the production of debris.
    Type: Grant
    Filed: November 2, 2010
    Date of Patent: May 21, 2013
    Assignee: Raytheon Company
    Inventors: Darin S. Williams, Richard J. Wright
  • Patent number: 8445822
    Abstract: A one-piece extended dome having a spanning angle greater than 180 degrees. The dome is integrally formed of a Nano/Nano class Nanocomposite Optical Ceramic (NNOC) material. The extended dome comprises seamless first and second non-complementary geometric shapes, such as a first spherical geometry and a second conical or ogive geometry. The Nano/Nano class NNOC material comprises two or more different chemical phases (nanograins) dispersed in one another, each type having a sub-micron grain dimension in at least the direction of light transmission. The material is a true NNOC material in that all of the constituent elements have sub-micron grain dimensions, there is no host matrix.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: May 21, 2013
    Assignee: Raytheon Company
    Inventor: Wayne L. Sunne
  • Patent number: 8415596
    Abstract: A method for determining a location of a flying target included identifying and measuring the target by at least two seeker systems disposed at a distance from one another. The position of the target relative to at least one of the two seeker systems is determined from measurement data derived therefrom. The position of the target is measured inconspicuously and without active radiation, in that the seeker systems are data-networked, passive target tracking systems for missiles, which autonomously track the target and align the missile with the target. The measurement data determined by the data-networked seeker systems are combined, and the location of the target is determined from the combined data.
    Type: Grant
    Filed: January 21, 2011
    Date of Patent: April 9, 2013
    Assignee: Diehl BGT Defence GmbH & Co. KG
    Inventors: Raimund Dold, Thomas Kuhn, Wilhelm Hinding
  • Patent number: 8405011
    Abstract: A target tracking device incorporating a Position Sensitive Detector (PSD) 1 is described. A target is illuminated by a laser of a suitable wavelength. The target reflects the laser radiation and the reflected radiation is incident on a flying vehicle carrying a target tracking device. The PSD in the device outputs a signal representative of the position of the incident laser spot. The output signal is input into control electronics, the control electronics incorporating a resistive transimpedance amplifier. A higher than usual bias voltage is applied to the PSD yielding improved pulse response of the target tracking device. Therefore, the tracking device is particularly suited for use with a target marking laser having a short pulse duration.
    Type: Grant
    Filed: January 4, 2010
    Date of Patent: March 26, 2013
    Assignee: Selex Galileo Ltd.
    Inventor: Michael Charles Sharpe
  • Patent number: 8378276
    Abstract: A method and apparatus for guiding a vehicle to intercept a target is described. The method iteratively estimates a time-to-go until target intercept and modifies an acceleration command based upon the revised time-to-go estimate. The time-to-go estimate depends upon the position, the velocity, and the actual or real time acceleration of both the vehicle and the target. By more accurately estimating the time-to-go, the method is especially useful for applications employing a warhead designed to detonate in close proximity to the target. The method may also be used in vehicle accident avoidance and vehicle guidance applications.
    Type: Grant
    Filed: March 8, 2007
    Date of Patent: February 19, 2013
    Assignee: Lockheed Martin Corp
    Inventor: Vincent C. Lam
  • Patent number: 8378880
    Abstract: An object of interest in a cloud of objects is identified by RF and IR sensing. The RF and IR signals are separately discriminated to determine the probability that the RF tracked object is one of a predetermined number of possible object types, and the IR tracked object is one of the possible object types. Joint probabilities are calculated for all pairs of RF and IR signals and all objects, and the joint probabilities are normalized. Marginal probabilities of the joint RF/IR discrimination results are calculated to produce a vector set of marginal optical probabilities. The vector set is normalized over all object types to thereby produce a vector set of normalized marginal optical probabilities. The object of interest is selected to be the IR object of said vector set of normalized joint optical probabilities with the highest probability of being the object type of interest.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: February 19, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Jeffrey B. Boka, Naresh Raman Patel, Joseph P. Tadduni
  • Publication number: 20130001354
    Abstract: A sensor system uses ground emitters to illuminate a projectile in flight with a polarized RF beam. By monitoring the polarization modulation of RF signals received from antenna elements mounted on the projectile, both angular orientation and angular rate signals can be derived and used in the inertial solution in place of the gyroscope. Depending on the spacing and positional accuracies of the RF ground emitters, position information of the projectile may also be derived, which eliminates the need for accelerometers. When RF signals of ground emitter/s are blocked from the guided projectile, the sensor deploys another plurality of RF antennas mounted on the projectile nose to determine position and velocity vectors and orientation of incoming targets.
    Type: Application
    Filed: June 30, 2011
    Publication date: January 3, 2013
    Inventors: A. Douglas Meyer, Mostafa A. Karam, Charles A. Lee, Charles H. Volk
  • Patent number: 8288697
    Abstract: A method for commanding an attitude change of a boosting missile to tend to maintain good communication link quality includes the step of precalculating attenuation of a link between the boosting missile and a ground station in the presence and absence of multiple missile plumes. If the actual link attenuation is less than the precalculated attenuation in the absence of multiple missile plumes, no attitude change is commanded. If the actual link attenuation exceeds the precalculated value, the actual link attenuation is compared with the calculated attenuation in the presence of multiple missile plumes. If the calculated multiple plume RF attenuation is less than the actual link attenuation, the attenuation is deemed to be caused by some factor other than multiple plume attenuation, and produces a flag for commanding a change in attitude.
    Type: Grant
    Filed: December 29, 2009
    Date of Patent: October 16, 2012
    Assignee: Lockheed Martin Corporation
    Inventor: David E. Wolf
  • Publication number: 20120199690
    Abstract: A method for onboard determination of a roll angle of a projectile.
    Type: Application
    Filed: November 22, 2009
    Publication date: August 9, 2012
    Applicant: OMNITEK PARTNERS LLC
    Inventors: Jahangir S. Rastegar, Carlos M. Pereira
  • Publication number: 20120181374
    Abstract: A technique employing one or more conformal, spiral antenna for use in a vehicle such as a missile. The technique includes both an apparatus and a method. The apparatus includes a radome or missile body and a conformal, spiral antenna mounted in the radome or missile body. The method is one for use in operating a missile, comprising transmitting and receiving signals through a plurality of conformal, spiral antennae mounted in a radome or missile body. This may include in some variants transmitting and receiving signals through a plurality of conformal, spiral antennae mounted in a radome or missile body; and guiding the missile from information obtained from signals receive through the antennae.
    Type: Application
    Filed: July 30, 2010
    Publication date: July 19, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventor: Brett A. Williams
  • Publication number: 20120169524
    Abstract: The disclosed approach provides a low-cost approach by employing a single channel receiver for a direction-finding missile, rather than a conventional four-channel system. It employs interferometry techniques. The proposed approach leverages orthogonal waveforms and pseudorandom noise (PN) codes. This is a low-cost approach for a single channel direction finding system by leveraging orthogonal waveforms and interferometric techniques.
    Type: Application
    Filed: December 29, 2010
    Publication date: July 5, 2012
    Inventors: Mark B. Yeary, James R. Toplicar, Paul E. Doucette, Eleanor Foltz
  • Patent number: 8153943
    Abstract: A tornado disarming network includes a command center, tornado detection systems, and tornado busting missile launch sites in communications with the command center. Tornado busting missiles are at the tornado busting missile launch sites. Each tornado busting missile includes a radar, a guidance system and a solid rocket motor for propelling the missile toward the tornado. A thruster control system causes the tornado busting missile to travel upward within the tornado upon reaching the tornado. An explosive discharge system explodes within the tornado to generate heat for causing the air within the tornado to expand, thereby weakening the tornado.
    Type: Grant
    Filed: July 6, 2009
    Date of Patent: April 10, 2012
    Inventor: Riley H. Nelson
  • Patent number: 8138982
    Abstract: The present invention is a multi-element anti-jamming (A/J) antenna array. The antenna array includes a first multi-band GPS edge-slot antenna and a second multi-band GPS edge-slot antenna. The first edge-slot antenna and the second edge-slot antenna are configured for implementation within at least one of an artillery shell and a munition. The first edge-slot antenna and the second edge-slot antenna are each further configured for supporting L-band frequencies.
    Type: Grant
    Filed: June 26, 2007
    Date of Patent: March 20, 2012
    Assignee: Rockwell Collins, Inc.
    Inventors: James B. West, Lee M. Paulsen, Daniel N. Chen, Kendra L. Kumley
  • Patent number: 8130137
    Abstract: A method and a system for sensing a boosting target missile, estimate position and velocity and boost acceleration parameters of the target missile, and control an interceptor missile to the target missile. A boost-phase missile target state estimator estimates at least acceleration, velocity, and position using an acceleration template for the target vehicle. The nominal template is incorporated into an extended Kalman filter which corrects the nominal template acceleration with the filter states to predict future thrust acceleration, velocity and position. The correction can compensate for motor burn variations and missile energy management (lofted/depressed trajectory).
    Type: Grant
    Filed: October 8, 2007
    Date of Patent: March 6, 2012
    Assignee: Lockheed Martin Corporation
    Inventors: Thu-Van Luu, Jeffrey B. Boka, Purusottam Mookerjee, Michael J. Harcourt
  • Patent number: 8119957
    Abstract: A submunition is formulated for destroying a target in a target area. Accommodated in a casing are a signal processing unit connected to a radar antenna and/or an infrared sensor and/or another target-detecting sensor. The submunition further has target recognition software and a charge provided with a covering. To increase the versatility of use and to simultaneously improve detection and decision certainty and reliability, the target recognition software has a software interface for the transfer of at least one parameter specific to the target area.
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: February 21, 2012
    Assignee: Diehl BGT Defence GmbH & Co. KG
    Inventor: Harald Wich
  • Patent number: 8119956
    Abstract: A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a ‘missile in a missile’ architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE-rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until “the last second” reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance.
    Type: Grant
    Filed: September 21, 2009
    Date of Patent: February 21, 2012
    Assignee: Raytheon Company
    Inventors: Richard Janik, Doron Strassman
  • Publication number: 20120037749
    Abstract: Methods and apparatus for launching an effector according to various aspects of the present invention may include a fire control system. The fire control system may be responsive to a sensor, such as a radar, and may be connected to the effector, such as via a launcher. The file control system may be adapted to generate a fire control solution according to the data from the sensor, initiate a launch of the effector, and provide the fire control solution to the effector after initiating the launch.
    Type: Application
    Filed: May 14, 2008
    Publication date: February 16, 2012
    Inventors: David A. Lance, Steven T. Siddens
  • Patent number: 8106340
    Abstract: A method for guiding a multistage interceptor missile toward a target missile that may transition from a boost mode to a ballistic mode during the engagement. The method comprises the steps of tracking the position of the target missile with a sensor, generating a predicted intercept point and time, and loading the predicted intercept point and time into the interceptor missile guidance system. The interceptor missile is launched and transition is made to the second stage of propulsion of the interceptor missile. Second-stage midcourse guidance acceleration commands are generated in response to an elevated predicted intercept point generated using the Runge-Kutta integration method working on predicted target missile position, velocity, and acceleration. During third stage propulsion said interceptor missile is guided toward an updated predicted intercept point of the target missile. During fourth stage, the kinetic warhead effects a hit-to-kill intercept of the target missile.
    Type: Grant
    Filed: March 2, 2009
    Date of Patent: January 31, 2012
    Assignee: Lockheed Martin Corporation
    Inventors: Frederick U. Diaz, Jeffrey B. Boka
  • Publication number: 20120012690
    Abstract: A matrix of explosive cells can include plural explosive cells formed in an array in a common substrate. Each cell can be formed as a recess filled with explosive material. An ignition device has an addressable ignition source for each cell. This matrix can be used in combination with a projectile guidance system. The projectile guidance system includes an antenna, a transceiver and a control processor. A method of guiding a projectile can include firing a projectile at a target, tracking the projectile and the target, determining a desired change in a flight path of the projectile, transmitting guidance commands to effect the desired change in the projectile's flight path to the projectile, receiving the guidance commands onboard the projectile and selectively igniting an explosive cell in a matrix of addressable explosive cells contained in a common substrate using the guidance commands.
    Type: Application
    Filed: February 19, 2009
    Publication date: January 19, 2012
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: Christian Adams, Kenneth S. Gurley, Tara Y. Rohter, Patrick A. Nelson