Abstract: Disclosed are examples of systems, apparatus, methods and computer program products for locating unmanned aerial vehicles (UAVs). A region of airspace may be scanned with two scanning apparatuses. Each scanning apparatus may include one or more directional Radio Frequency (RF) antennae. The two scanning apparatuses may have different locations. Radio frequency signals emitted by a UAV can be received at each of the two scanning apparatuses. The received radio frequency signals can be processed to determine a first location of the UAV.

Abstract: A mounting device that is used to suspend items in a specific location inside the cavity of a tubular structure, such as a munition, is disclosed. The mounting device includes: a pedestal for leading the insertion of the mounting device into a cavity of a munition and a skeletal frame. The skeletal frame defines an opening therein for holding an article inside the outermost portion of the skeletal frame. In some cases, the skeletal frame may have a fixed configuration. In other cases, the skeletal frame may be collapsible and expandable so that it may be inserted into a cavity of a munition having an obstruction therein. Methods of inserting and mounting an article inside an internal explosive cavity of a munition are also disclosed.

Abstract: An imaging system comprises an imaging platform, a camera operatively connected to the imaging platform, and a controller operatively connected to control the imaging platform and the camera. The controller includes machine readable instructions configured to cause the controller to perform a method.

Abstract: A method of making a non-solid state polyester that includes: a) reacting terephthalic acid and ethylene glycol; b) removing the water continuously; c) polymerizing the monomers and oligomers in vacuum conditions at a temperature to form molten polyester having an IV (intrinsic viscosity) of about 0.7 to 0.

Abstract: A system may include emitters configured to emit radiation at a first wavelength of electromagnetic (EM) radiation and a second wavelength of EM radiation towards a biological tissue, and receivers configured to receive responses to the first and second wavelengths of EM radiation after the wavelengths of EM radiation interact with the biological tissue. The system may also include a signal mixer unit configured to perform operations that include replicate and mix first signals representative of the responses to the first wavelength of EM radiation received by the receivers and second signals representative of the responses to the second wavelength of EM radiation received by the receivers to generate a set of spectro-spatial responses, replicate and mix the spectro-spatial responses to generate markers, and replicate and mix the markers and user-selected markers to output a sequence associated with characterization of the biological tissue.

Abstract: The embodiments relate to a conformal, sometimes referred to as aerodynamic, nose cone, and in particular to a hollow conformal nose cone that is transparent to electromagnetic radiation of a predetermined wavelength, or wavelengths, and that comprises a variable thickness such that the electromagnetic radiation received on an outer surface of the nose cone forms a predetermined beam pattern within the nose cone. Also disclosed are mechanisms for generating such hollow conformal nose cones.

Abstract: An apparatus and a method capable of accurately recognizing that a person will appear on a road and certainly notifying the person that an autonomous moving body has recognized a place where the person will appear are disclosed. An apparatus according to an embodiment of the present disclosure detects, as a recognition target, a person appearance area, in which a person will appear, formed by a recognition target presentation apparatus on a road and presents, to the person, a result of recognition indicating that the autonomous moving body has recognized the person appearance area as a result of the detection of the recognition target.

Abstract: A vehicle, driving system and method for driving a vehicle is disclosed. The driving system includes a radar system, a processor and an autonomous driving system. The radar system obtains an SAR measurement of a static object in an environment of the vehicle. The processor obtains a first estimate of a location of the vehicle in the environment, obtains from a database a representation of a static object in the environment associated with the first estimate of the location, and compares the SAR measurement of the static object to the representation of the static object from the database to obtain a second estimate of the location of the vehicle. The autonomous driving system drives the vehicle through the environment based on the second estimate of the location of the vehicle.

Abstract: A collision avoidance system includes a processor configured to determine first and second positions of an intruder in first and second images, respectively, determine an angular position change of the intruder by comparing the first and second positions, determine a rate of change of a line of sight angle from an aircraft to the intruder based on the angular position change and a time between the first and second images, determine a rate of change of the angular size of the intruder based on a difference in angular size of the intruder from the first to second image and the time between the first and second images, and provide an alert to an operator of the aircraft in response to the ratio of the rate of change of the line of sight angle and the rate of change of the angular size of the intruder being less than a threshold.

Abstract: In a method of guiding a missile in flight to a target (FIG. 1), the location of the missile and the range to the target are measured at a plurality of moments during the flight of the missile (step 10). The location of the target is calculated from the measured ranges and the measured missile locations (step 20). A required velocity vector angle is calculated from the calculated location of the target and a guidance law (step 30). A lateral acceleration required to provide the missile with a velocity oriented to the target at the required velocity vector angle is calculated for the missile (step 40). The missile is caused to accelerate with the calculated lateral acceleration, so that the missile to follows a trajectory according to the guidance law (step 50).

Abstract: An optical unit with a shake correction function may include an optical module having a movable body holding an optical element, a support body swingably supporting the movable body around two axial lines perpendicular to an optical axis of the optical element, and a swing drive mechanism structured to be capable of reciprocatedly swinging the movable body with respect to the support body around the two axial lines, and a rolling correction drive mechanism structured to be capable of reciprocatedly turning the optical module around the optical axis. The rolling correction drive mechanism includes a single phase motor in which the number of salient poles of a stator core around which a stator coil is wound is two times of the number of magnetic poles of a rotor magnet.

Abstract: An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT causing the Internal Air Injection Unit (A.I.U.) to supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.

Abstract: A method of controlling a projectile includes initiating an execution mode if a roll control authority parameter is outside of a pre-determined operating range for a projectile. The execution mode includes bypassing a guidance command and sending a modified command to execute a coning maneuver to improve control response of the projectile. A projectile control system includes a processor operatively connected to a memory. The memory has instructions recorded thereon that, when read by the processor, cause the processor to execute the method operations described above.

Abstract: According to one embodiment, a tracking apparatus includes a spherical body, 1st to 3rd gimbals, a movable body, three or more spherical driving units, a hold unit, a target position identifying unit, 1st to 4th angle sensors, a rotation spring driving unit, a moving unit, a transmission unit, and a control unit. The rotation spring driving unit returns the third gimbal to a center of a rotation range of the third gimbal. The moving unit moves a movable lens to set a distance between a fixed lens and the movable lens. The control unit causes the spherical driving units to swing the movable body based on the position data and the 1st to 4th angles, reorients the movable body to point in a desired direction, and controls the distance.

Abstract: A system comprises a processing system, a laser system, a telescope system, a detector system and optical systems operatively arranged such that the laser system may be capable of outputting multiple wavelengths to a common telescope system, and the detector system is capable of receiving signatures from the same telescope system, under the control of a control system. The processor system processes signals received from the detector system to determine substances identified by known signatures. For example, a plurality of detectors in the detector system each receive a range of wavelengths of the signatures received by the telescope system. For example, a variable beam diverger and variable beam expander operatively control expansion and divergence of the output the laser system. For example, a beam reducer and lenslet array may operatively transmit signatures via optical fiber bundle to one or more of the detectors.

Abstract: A new fuze that reduces projectile miss-distance to a target, by correcting for discrepancies in anticipated round velocities through its flight. As a result, the fuze-equipped projectile is nominally aimed at a target and maintains improved accuracy relative to a conventional round. The fuze adjusts for the discrepancies in velocity by using an internal electric motor to mechanically actuate a drag-altering surface on the fuze body. In order to adjust for errors in the anticipated velocity, the fuze compares its preprogrammed velocity to its actual velocity at a given point in time during flight. An anticipated velocity table versus time in flight is constantly referenced so that appropriate adjustments in velocity can be made.

Abstract: A method for correcting spatial response for an imaging Fourier transform spectrometer comprises the following steps: a prior step of calculation of the equalization parameters comprising a gain and an offset from data forming calibration scenes; a step of determination of equalization coefficients at a so-called pseudo superpixel level determining the gains and offsets at macropixel level from the data from a raw image that are collected by the imaging spectrometer in image mode, and gains and offsets determined in the prior step; and a step of equalization at pseudo superpixel level, applying the equalization coefficients to a macropixel from an acquisition in the interferogram mode of the imaging spectrometer in order to restore an equalized interferogram.

Abstract: A method of mapping a target region image to a referenced image includes steps of acquiring the target region image. The method also includes acquiring the referenced image overlapping the target region image. The method further includes determining a number of common subregions in an intersection of the referenced image and the target region image, determining offsets between the common subregions, computing a distortion map of the target region image over the intersection, and remapping the target region image to match the reference image. The method can be utilized in a Unmanned Aerial Vehicle (UAV) and the target image can be a SAR image.

Abstract: An unmanned aerial vehicle with a camera and conventional sensors, where the processor navigates the vehicle based at least in part on the image data and the sensor data. A method for navigating an unmanned aerial vehicle where a processor navigates the vehicle based at least in part on image data corrected by traditional sensor data.

Abstract: In certain aspects, this invention is a “control system” that detects and minimizes (or otherwise optimizes) an angle between vehicle centerline (or other reference axis) and vehicle velocity vector—as for JDAM penetration. Preferably detection is exclusively by optical flow (which herein encompasses sonic and other imaging), without data influence by navigation. In other aspects, the invention is a “guidance system”, with optical-flow subsystem to detect an angle between the vehicle velocity vector and line of sight to a destination—either a desired or an undesired destination. Here, vehicle trajectory is adjusted in response to detected angle, for optimum angle, e.g. to either home in on a desired destination or avoid an undesired destination (or rendezvous), and follow a path that's ideal for the particular mission—preferably by controlling an autopilot or applying information from navigation.

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.

Abstract: A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

Abstract: A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point.

Abstract: A dual-mode sensor uses the active guidance radiation as a “guide star” to generate a wavefront error estimate for the primary optical element in-situ without interfering with the generation of either the active guidance or passive imaging guidance signals. An array of optical focusing elements performs the normal function of spatially encoding an angle of incidence of the active guidance radiation at an entrance pupil onto an active imaging detector. The array also performs an additional function of spatially encoding wavefront tilt deviations emanating from sub-pupils of an exit pupil onto the active imaging detector. A processor processes the electrical signals from the imaging detector in accordance with the respective spatial encodings to generate an active guidance signal and the wavefront error estimate for the primary optical element.

Abstract: A pointing device is provided for directing electromagnetic radiation along a line of sight within a flight vehicle. The pointing device includes a beam deviation structure; a rotation assembly configured to support the beam deviation structure such that the beam deviation structure is pivotable about the rotation axis; and a nod gimbal configured to support the rotation assembly and the beam deviation structure such that the rotation assembly and the beam deviation structure are pivotable about a nod axis.

Abstract: Guided airborne weapons fired in a salvo against multiple targets are deconflicted by performing a scene correlation of multiple cued targets to TLOs acquired by the seeker's imaging sensor to track a target package. If the weapon is provided with a multimode seeker, target cues for a common designated target and a common SAL code are provided to each weapon. Each weapon uses its SAL sensor to detect and process a SAL return to verify the common SAL code and augment their scene correlations by fixing the TLO track file of the common designated target to the cued track file associated with the designated target. At terminal, each weapon commits to a particular target by referencing its assigned target to the tracked target package. Correlation to multiple targets in the target package makes the acquisition and tracking process more robust and reduces targeting ambiguity. Furthermore, a single SAL designation can improve the tracking of all the weapons to their respective targets.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

Abstract: A micro designator dart engages a target to allow for designation and tracking of the target by transmitting a radio-frequency identification code. The housing of the micro designator dart is configured to enclose its components and deform upon impact with a target to allow a target-engaging member to physically attach the micro designator dart to the target. Also upon impact with the target, an impact-sensitive triggering mechanism in the micro designator dart activates a power source, causing a transmitter to send a predetermined coded infrared signal to the seeker unit of a precision guided munitions system. The micro designator dart may also include a self-destruct device.

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract: By sharing tasks between the CV and the KVs, the MKV interceptor provides a cost-effective missile defense system capable of intercepting and killing multiple targets. The placement of the acquisition and discrimination sensor and control sensor on the CV to provide target acquisition and discrimination and mid-course guidance for all the KVs avoids the weight and complexity issues associated with trying to “miniaturize” unitary interceptors. The placement of either a short-band imaging sensor and headlamp or a MWIR sensor on each KV overcomes the latency, resolution and bandwidth problems associated with command guidance systems and allows each KV to precisely select a desirable aimpoint and maintain track on that aimpoint to impact. An implicit divert and attitude control system (DACS) using tow or more divert thrusters performs KV divert and attitude maneuvers to respond to the command guidance pre-handover and to maintain track on the aimpoint to terminal intercept post-handover.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

Abstract: A method for correcting a trajectory of terminally guided ammunition is provided. In order to achieve a high probability of hits, in particular when firing in bursts (continuous fire, rapid single shot fire), it is provided that every individual ammunition is addressed separately. The “imprinting” is performed based on the beam rider guidance principle of terminally guided ammunition. Every individual ammunition reads only the guidance beam identified for this ammunition and can, using additional information, determine its absolute roll attitude in space in order to achieve the proper triggering of the correcting propulsion unit.

Abstract: A steerable-light-path optical device includes a light transceiver having an external light path associated therewith, and a path-steering device that controls the direction of the light path relative to a steering axis. The path-steering device has a first beam-deviation optical element including a first prism structure having a first diffraction grating thereon, and a second beam-deviation optical element including a second prism structure having a second diffraction grating thereon. The steering axis passes through the first and second beam-deviation optical elements. A rotational drive is operable to rotate at least one of the first beam-deviation optical element and the second beam-deviation optical element, and preferably both of the beam-deviation optical elements, about the steering axis.

Abstract: A flying object includes a lift and displacement motor which has a combustible propelling charge and direct thrust flight control and can ensure the lift and displacement of the flying object in an observation position for which the flying object is at least approximately vertical with the rear part thereof oriented downwards; an attitude motor with a combustible propelling charge and conventional thrust vector control; and an observation unit which is arranged in the rear part of the flying object.

Abstract: An apparatus for detecting radiation includes an entry window configured to receive radiation from a target, the entry window having an outer surface and an inner surface, such that the outer surface is not parallel to the inner surface. The apparatus further includes a radiation transmission assembly configured to receive at least a portion of the radiation received by the entry window. The apparatus further includes a radiation sensor configured to receive at least a portion of the radiation from the radiation transmission assembly.

Abstract: By sharing tasks between the CV and the KVs, the MKV interceptor provides a cost-effective missile defense system capable of intercepting and killing multiple targets. The placement of the acquisition and discrimination sensor and control sensor on the CV to provide target acquisition and discrimination and mid-course guidance for all the KVs avoids the weight and complexity issues associated with trying to “miniaturize” unitary interceptors. The placement of a short-band imaging sensor on each KV overcomes the latency, resolution and bandwidth problems associated with command guidance systems and allows each KV to precisely select a desirable aimpoint and maintain track on that aimpoint to impact.

Abstract: The present invention provides a MKV interceptor including multiple kill vehicles with autonomous management capability and kinematic reach to prosecute a large threat extent. Each KV can self-manage its own KV deployment and target engagement for a determined target volume assigned by a designated master KV. At least one KV is master capable of managing the post-separation of all of the KVs without requiring updates to the mission plan post-separation. The autonomous capability and increased kinematic reach provides for a more efficient use of boosters and more effective engagement of the threat.

Abstract: A method of tracking a target. The method includes the steps of acquiring a first spectral image of a scene that includes the target, designating a spectral reference window, in the first spectral image, that includes a respective plurality of pixel vectors, acquiring a second spectral image, of the scene, that includes a respective plurality of pixel vectors, and hypercorrelating the spectral reference window with the second spectral image, thereby obtaining a hypercorrelation function, a maximum of the hypercorrelation function then corresponding to a location of the target in the scene.

Abstract: Disclosed are antenna embodiments and air vehicles so equipped that include a first antenna component, and a second antenna component, separated by a free space gap, where the antenna embodiments are adapted to capacitively couple the first antenna component and the second antenna component across one or more portions of the free space gap and where the first antenna component member has a degree or axis of rotation, relative to the second antenna component.

Abstract: Systems and methods for contiguously and accurately updating target object information during an entire target engagement period are provided. The target tracking system includes a database for storing starfield information, an optical beam source configured to illuminate one or more optical beam pulses, first and second camera systems, and a processor. The processor instructs the first camera system to track the object based on recordation of the tracked object, instructs the second camera system to stabilize the tracking image based on the instructions sent to the first camera system, and determines inertial reference information of the tracked object based on the stabilized image and starfield information associated with the stabilized image.

Abstract: An apparatus for directing light beams onto a target comprising a beam splitter for splitting a main beam into a first split beam and a second split beam; a first beam path for the first split beam, the first beam path including a first aperture, a first lens and a second lens; a second beam path for the second split beam, the second beam path including a second aperture, a third lens and a fourth lens; a plurality of mirrors arranged such that the first split beam and the second split beam intersect at the target. An apparatus can also include means for placing a target in the image plane of a first aperture and a second aperture.

Abstract: Method for guiding a rocket (1) to a target, wherein, the rocket (1) being equipped with automatic guiding means with an image-formation device (10) and means for correction of the trajectory (11): the target is acquired by a sighting device and its position is determined; the sighting device and the rocket image-formation device (10) are brought into line; the images of the rocket image-formation device (10) are stabilized; a guiding law is produced; the rocket (1) is launched; and the rocket is guided according to this law until the rocket itself acquires the target.

Abstract: Applicants' ATR system is weather-agile because it is comprised of a primary target sensing means that is capable of surveilling the target scene in foul or fair weather, and a secondary target sensing means that is also capable of sensing targets in various weather. The primary and secondary sensing means communicate through a control center so that ultimately, among several weapons available, the most strategically located and equipped weapon is activated for the destruction of a selected target, given the weather. The control center accomplishes the communication by receiving the sensed target signature from the primary sensing means, processing the signature using database already resident in the center and transmitting the processed target signature to the weapon possessing the greatest potential for successfully destroying the target.

Abstract: The present invention relates to a projectile seeker which comprises: (a) A hollow in the projectile for accommodating a light sensor; (b) A light sensor located within said hollow for sensing light which is emitted or reflected from a target, and for producing an electronic signal upon sensing such emitted light; and (c) A longitudinal shaped opening at the slanted front-side surface of the projectile for enabling a shaped field of view to said light sensor which is limited by the boundaries of said opening, the opening width varies in a direction from the front to the back of the projectile in order to cause said electronic signal to depend on the spinning of the projectile and to be proportional to the orientation of the projectile with respect to the object.

Abstract: A projectile navigation system operable within an extremely high G-shock loading environment during the launch phase may include a set of Kalman filters configured to repeatedly calculate a navigational solution by solving a set of non-linear equations of motions of the projectile utilizing a current parameter vector, position, velocity, and attitude of the projectile. The system may include a suite of solid state sensors to calibrate the Kalman filter equations. If desired, the system may also include a satellite based positioning-determining (SBPD) attitude determination system configured to update the state of the host projectile by making real time attitude measurements of the projectile, and a parameter estimator configured to estimate and update a parameter vector of the host projectile. An external guidance and control processor may be used to generate guidance and control signals, enabling real time navigation of the host projectile.

Abstract: A plurality of sensor vehicles collect imaging data from an assigned location of a target region having targets and non-targets. The imaging data may be combined based on its location and the combined data is matched to a threat object map to identify the actual targets from the non-targets. In some embodiments, the sensor vehicles may be redirected to collect velocity and/or range information on the identified targets.

Abstract: Systems and methods for contiguously and accurately updating target object information during an entire target engagement period are provided. The target tracking system includes a database for storing starfield information, an optical beam source configured to illuminate one or more optical beam pulses, first and second camera systems, and a processor. The processor instructs the first camera system to track the object based on recordation of the tracked object, instructs the second camera system to stabilize the tracking image based on the instructions sent to the first camera system, and determines inertial reference information of the tracked object based on the stabilized image and starfield information associated with the stabilized image.

Abstract: A munition is presented which includes an integrity verification system that measures the integrity of the munition. When an integrity threshold is not met, engagement of the munition with a predetermined target is aborted. Also presented is a methodology for gating the engagement of the munition with the target. The methodology includes performing an integrity check of the munition after it is deployed. The method further includes aborting the engagement of the target when the integrity check of the munition fails.

Abstract: A system includes an optical system having a curved window with anamorphic symmetry about a first plane and a second plane perpendicular to the first plane. The window may be, for example, in a flight vehicle such as a missile. An optical corrector is adjacent to a curved inner surface of the window and has an optical corrector shape responsive to a shape of the window. The optical corrector has anamorphic symmetry about the first plane and the second plane. A sensor is disposed to receive an optical ray passing sequentially through the window and the optical corrector.

Abstract: Method for guiding a rocket (1) to a target, wherein, the rocket (1) being equipped with automatic guiding means with an image-formation device (10) and means for correction of the trajectory (11):