227results about "Direction controllers" patented technology

The Portable Digital Twin Robotic System based on Computer Vision for the Identification, Tracking, and Destruction of Suicide Drones is an innovative system that autonomously identifies, tracks, and destroys suicide drones by leveraging Digital Twin and computer vision technology. This system analyzes visual data using artificial intelligence algorithms and performs precise positioning in real-time. Aided by the Digital Twin, the precise simulation of the system's dynamics and movement enables the optimization of paths and precise control of the robot, while the real-time communication between the digital model and the physical robot provides the capability for immediate updates of control algorithms and predictive maintenance. The portable design and the capability to be connected to various types of weapons make this system suitable for installation on military and non-military platforms and improves the security of sensitive areas.

The invention refers to a counter countermeasures device, for use in an anti-aircraft combat. In one embodiment the CCM device together with an anti-aircraft weapon system forms an air defense system. The counter countermeasures device is configured for generating and emitting electromagnetic radiation of appropriate wavelengths and is capable of operating in spoof and jam mode and switching between both modes. The mode of operation is dependent on the selection of the output power of the EM source unit and the distance to the target. The selection of the output power may be done with a mechanical cover or with an electronic solution, decreasing driving current of the EM sources. With the CCM device the anti-aircraft missile launch warning and detection system installed on aircrafts are deceived and the countermeasures are released. With the use of the CCM device the efficiency of the anti-aircraft combat is highly improved, i.e. the probability of the target hit is highly improved.

The invention provides a seeker target positioning method and system based on image recognition, electronic equipment and a storage medium, and relates to the technical field of seeker target localization. The method comprises the steps that a target optical image sequence is obtained, and the angular displacement amount and the angular velocity variation amount of a seeker platform are collected; extracting a target contour boundary point set from the continuous frames of the image sequence, and calculating the local curvature variation and the overall shape change rate of the contour; combining the two into a deformation characteristic vector, and establishing a mapping relation to generate a track offset vector; driving the deflection shaft of the fast reflector to perform compensation motion along the reverse direction of the trajectory offset vector, and fusing the angular displacement and the angular velocity variation to generate a real-time correction parameter; the target contour deformation characteristics are dynamically matched with the geometrical relationship of the reflector compensation vector, the stable positioning coordinates are calculated after the compensation vector form is adjusted through real-time correction parameters, and the positioning precision and stability of the high-speed moving target under strong dynamic interference can be improved.

A guided munition and associated method, which may be implemented by a computer program product, is provided. The guided munition may have an annular folded optic (AFO), wherein at least a first portion of the AFO may be, at least partially, on a wing of the guided munition. The AFO may be transversely segmented to enable the AFO to move between a collapsed position and a deployed position. There may be a first segment and a second segment that selectively interface in response to at least one instruction to move the first segment and the second segment closer to each other. There may be an interface plane, wherein the interface lies along the interface plane, that intersects a central axis at a location outside the body of the AFO. This allows for a dual mode seeker with both the SAL and an image sensor located behind a warhead.

A calibration assembly for a guided vehicle. The calibration assembly includes an orientation marker that operably engages with a first guidance apparatus of the guided vehicle. The calibration assembly also includes an imaging assembly that operably engages with and is in electrical communication with a second guidance apparatus of the guided vehicle. When the imaging assembly captures the orientation marker at a translated position for at least one cycle, the imaging assembly calibrates a rotational displacement between a first guidance direction of the first guidance apparatus and a second guidance direction of the second guidance apparatus based on an angular displacement of the orientation marker measured between a zeroed position denoting the first guidance direction and the translated position.

Aircraft multiple sensitive small micro-eye optical / IR (visible light and / or infrared) cameras distributed in many suitable places in the aircraft so that collectively they are able to visualize and scan all the surroundings. With AI analysis and processing, an integrated panoramic entire-scope view with some stereoscopic perception effect could gained. After few early trial-flights of each aircraft, AI should be able to unit images collected by all cameras into one integrated view of all surrounding universe and build up surrounding concentric virtual sensory shells. These cameras will act as micro eyes to detect all surroundings in space all the time. It spot any approaching anti-aircraft missile as a hot spot increasing rapidly in size and intensity so that AI will immediately activate appropriate protective maneuvers to escape the attaching missile(s) while avoiding accidents with any other surrounding aircrafts (objects). Suitable cable connections added for power supply and information sharing to central data controller processor controlled by AI. For existing aircrafts, it could added as add-on camera clusters with suitable cable connections. For future newly manufactured aircrafts, it should added to design in a better and proper way. This innovation could use also in many other military and civil industries.

A computer-implemented method for generating a feasibility indication indicative of the feasibility of a weapon carried on an aircraft in flight to successfully engage a target and / or the feasibility of a weapon carried on the target to successfully engage the aircraft, the method comprising: providing a database describing a performance envelope of the weapon; a) generating candidate polynomials, the polynomial variables being some or all of a group of weapon or aircraft firing condition parameters; and b) for each candidate polynomial, comparing the candidate polynomial to the performance envelope of the weapon using a least squares error criterion. calculating coefficients for the candidate polynomial that best fits the characteristics of the line; c) for each candidate polynomial, generating a candidate score according to the quality of the candidate polynomial's fit to the characteristics of the weapon's performance envelope; d) applying a genetic algorithm to the candidate polynomials and scores, including selecting the best scoring polynomial(s) and discarding the other polynomial(s), thereby identifying the best candidate polynomial and its coefficients; and e) repeating the identification process until all required characteristics of the performance envelope have a corresponding polynomial model. d) a method for generating coefficients characteristic of a performance envelope using a generic algorithm, wherein the generic algorithm has the form of a polynomial, uploading coefficients of the identified best candidate polynomial to the aircraft, selecting coefficients for the generic algorithm according to aircraft and target conditions by a reconfigurator on the aircraft containing the same generic algorithm, and generating a feasibility indication by the reconfigurator using the selected coefficients, the method comprising: i) defining a set of orders and / or types of candidate polynomials and dividing the defined set of orders and / or types into a plurality of subsets thereof; ii) iteratively applying the genetic algorithm simultaneously across a plurality of subsets of the defined set of orders and / or types of candidate polynomials, including iteratively applying the genetic algorithm across polynomial variables for each order and / or type of each subset of polynomials and saving the resulting respective coefficients and their scores;iii) using the saved coefficients and scores to select the best scoring polynomial(s) and discard other polynomial(s), thereby identifying the best candidate polynomials and their coefficients.

A system and method are provided for correcting targeting of indirect fire, including: acquiring values for a set of firing conditions, for each of the firing conditions determining statistical parameters of a covariance matrix of the firing conditions, including estimates of unit effects, standard deviations, and error correlations between registration and fire-for-effect (FFE) firing condition errors, wherein at least one correlation is less than one and greater than zero, acquiring a registration miss vector, generating from the statistical parameters a conditional correction matrix; and multiplying the conditional correction matrix by the registration miss vector to calculate a correction vector for FFE targeting.

A system comprising an unmanned aerial vehicle (UAV) (100) configured to transition (520) from a terminal homing mode (510) to a target search mode (530), responsive to an uplink signal (451) and / or an autonomous determination of scene change.

Automated methods may comprise automatically converting a ballistic trajectory of a projectile into a ballistic flight path. The ballistic flight path may comprise one or more segments. Each of the segments may comprise a plurality of coordinates. The coordinates may be located along the ballistic trajectory. The automated method may comprise automatically navigating an Unmanned Aerial Vehicle (UAV) along the ballistic flight path. The automated method may comprise automatically collecting environmental data along the ballistic flight path through employment of the UAV.

An apparatus includes at least one memory configured to store map data. The apparatus also includes at least one processor configured to segment one or more objects from one or more environment surfaces in the map data. The at least one processor is also configured to determine an offset based on a projectile drift. The at least one processor is further configured to generate a safety bounding box around each of the one or more objects using the offset.

A method and system for providing distance information from a sensor assembly to a flying target. The method comprises detecting the flying target and locking on the flying target by means of a tracking sensor. Directing a light beam at the detected flying target. Generating a movement pattern having a path around the detected flying target and controlling movements of the light beam so that the LOS of the light beam completes moving across the path of the selected movement pattern within a set timeframe. Generating distance information by measuring time- of-flight of the light beam, when being reflected from the flying target while moving the LOS of the light beam across the path of the movement pattern. The system comprises sensors and devices for performing the method.

The invention relates to a training system (1) for combating naval surface drones, this training system comprising: a remote operation system (2), a telecommunications system (3), one or more naval surface drones (5) which are configured to be operated simultaneously by the remote operation system (2), via the telecommunications system (3), to simulate an attack mission against one or more target ships (50), the number of naval surface drones (5) being in particular between 1 and 15, in particular between 3 and 10. Figure for the abstract: Fig. 1

The invention consists of a method for directing fire against targets where the position of at least one protected object is known, and including the following method steps: i.) measuring the position of the target, ii.) estimating the position of the target, iii.) estimating the speed of the target, iv.) categorizing the target, v.) calculating the trajectory of the target, vi.) deciding whether the target is heading towards a protected object or is passing by. The invention furthermore consists of a fire-control system for directing fire against an air target comprising at least one sensor, in order to measure the position of the air target as a function of time. The invention furthermore consists of a combat system including a firing device.

A modular radio frequency (RF) seeker may be modularly connected with a projectile having a diameter of about four inches or less. The modular RF seeker may have a plurality of RF antennas, wherein at least two RF antennas are spaced apart from each other at a distance that is less than one wavelength of a signal band of interest that is to be detected by the modular RF seeker. A modular connector that modularly connects with another portion of the projectile, wherein when modularly connected, the plurality of RF antennas are in operative communication with a guidance kit on the projectile that guides the projectile toward at least one signal jammer emitting a jamming signal at the signal band of interest.

Optical sensors and particularly gimbaled optical sensors transmit an active signal at a given wavelength and receive passive signals over a range of wavelengths while controlling pointing without benefit of measuring and locating the active signal return. The sensor includes a Tx / Rx Aperture Sharing Element (ASE) is configured to block the received active signal (e.g. reflections off a target in a scene) and process only the passive emissions. These optical sensors may, for example, be used with guided munitions or autonomous vehicles.

The invention relates to a detection device (1) for a missile, in particular a guided missile, comprising an optical device (2) which is designed to image radiation (5, 6) onto a detector plane (3) of a detector unit (4) of the detection device (1), wherein the detector unit (4) has at least two groups of detection regions (10, 11) which are sensitive to different wavelengths and / or wavelength ranges of the radiation (5, 6); the optical device (2) is designed to image radiation (5, 6) with at least two different wavelengths in the same spot size range, in particular with the same spot size, onto the detector plane (3), at least one spot (7, 8) being imaged unsharply onto the detector plane (3); and a control device (9) is designed to use a transformation algorithm, in particular an artificial-intelligence-based transformation algorithm, to transform the at least one spot (7, 8) which is imaged unsharply onto the detector plane (3) and has a first image sharpness into at least one spot with a second image sharpness, the second image sharpness being greater than the first image sharpness.

This invention discloses a method for correcting firing parameters in a closed-loop firing correction system suitable for conditions with very few satellite measurement points. It adds a rotational speed measuring device to the projectile system to measure the real-time rotational speed of the artillery projectile. Based on external ballistics theory, this invention utilizes muzzle rotation speed, ballistic speed, and measurement data (coordinates and velocities) from a limited number of ballistic points to propose a method for estimating the range and lateral deviations of a single projectile relative to the target point. This allows for the rapid determination of the launch angle and directional corrections, enabling artillery firing correction. This invention solves the key problem of how to quickly and accurately determine the firing parameter corrections of a closed-loop firing correction system when there are very few ballistic measurement points, greatly improving the adaptability and reliability of the closed-loop firing correction system under complex battlefield conditions and effectively enhancing the combat capability of the weapon system.

Seeker head (2) for a guided missile (1), comprising a detection device (3) having a first detection unit (6) for detecting infrared radiation and a second detection unit (8) for detecting radar radiation, wherein the detection unit (3) has a cooling device (14) configured to cool at least a first detection element (7) of the first detection unit (6), in particular a detector, and at least a second detection element (9) of the second detection unit (8), in particular an antenna element.

A system for guiding an unmanned aerial vehicle (UAV) to a target includes a map module and a path generation module. The map module obtains a map including a geographic region of interest. The path generation module receives a launch location and a target area and generates a flight path from the launch location to the target area based on the map. The UAV comprises a propulsion system and a sensor array. The sensor array includes at least one of a primary Global Navigation Satellite System (GNSS) receiver or a secondary Controlled Reception Pattern (CRPA) GNSS receiver. A path following module guides the UAV along the generated flight path. A path modifying module monitors input from the sensor array for a trigger event and modifies the flight path in response to detecting the trigger event.

A computer-implemented method for updating a configuration of a projectile launching device, the method comprising: determining a location of a target; determining a configuration of the projectile launching device to propel a projectile to collide with the target; receiving first data from a first passive sensor; determining a location of the propelled projectile based on the first data; and updating the configuration of the projectile launching device based on a determined relative difference of the location of the target and the location of the propelled projectile.

To determine the relative position (RL) of a missile (4) with respect to a target axis (18), a transmitter (24) emits a laser guidance field (26) with a pattern (30) varying and rotating around the target axis (18) along the target axis (18). The current intensity (IA1-3) of the laser guidance field (26) is recorded at three different measurement points (MP1-3) at known measurement positions (ML1-3) on the missile (4). From this, a difference (DPA,B) of polar angles (PW) between the two measurement points (MP1-3) of each pair (PA,B) with respect to the target axis (18) is determined for at least two different pairs (PA,B) of the three measurement points (MP1-3). The relative position (RL) is then determined as the offset (AL) of the roll axis (28) from the target axis (18) and the rotation angle (DW) of the missile (4) about the roll axis. (28) determined with respect to a zero angle (NW).To guide a guided missile (4), the above procedure is carried out for the guided missile as missile (4) and the guidance device (16) is controlled towards the target axis (18) depending on the relative position (RL). A missile assembly (22) includes the aforementioned transmitter unit (24), which emits the laser guidance field (26), and the missile (4), which determines the relative position (RL).

A method includes receiving, via a phased antenna array of a first wireless base station, signals from one or more signal sources in an environment; determining, via a signal processor based on the signals, a location of each of the one or more signal sources in the environment relative to the phased antenna array; determining a position of the first wireless base station in the environment; transmitting, via the phased antenna array, radar signals into the environment; receiving, via the phased antenna array, reflected signals from the environment; determining, using SAR, information about at least one of a distance and a movement of one or more physical objects in the environment; collecting the information about the at least one of the distance and the movement of the one or more physical objects in the environment from the SAR; and generating a 3D spatial map of the environment using the information.

A guidance system for a guided ammunition includes an inertial measurement unit (IMU) or other type of first sensor located on the guided ammunition, an optoelectronic / infrared (EO / IR) sensor located on the guided ammunition, and a guidance computer component (GCA) having a programmable real-time unit industrial communication subsystem (PRU-ICSS), the PRU-ICSS is in operational communication with a first sensor of an IMU or other type as well as a photoelectric / infrared sensor. The PRU-ICSS has a first programmable real-time unit (PRU), where the first PRU is programmed to receive and process input data from an IMU or other type of first sensor located on the guided ammunition; the PRU-ICSS also has a second PRU, where the second PRU is programmed to receive and process input data from an optoelectronic / infrared sensor located on the guided ammunition.

There is provided a drone comprising, a main body which is elongated and having a longitudinal axis, the main body being rotatable attached at one end of the elongated body to a propeller body with a shaft so that the main body and the propeller body are arranged to rotate in relation to each other, so that the propeller provides thrust in the direction of the shaft, where the main body rotates around its longitudinal axis, the drone comprising driving means mechanically connected to the shaft, the driving means driving rotation of the bodies in relation to each other, the drone comprising a control device arranged to control the speed of rotation of the driving means to control the thrust and further arranged to control the flight direction of the drone, where the drone is configured to rotate the propeller body at a first rotation speed that is greater than a second rotation speed of the main body in relation to an external frame of reference, the second rotation speed being referred to as roll speed, where the drone is configured such that the longitudinal axis of the main body has, during flight, an angle of attack greater than zero to the flight direction of the drone, said longitudinal axis rotating around the flight direction of the drone, the flight direction being in relation to the external frame of reference, where the rotation around the flight direction occurs with the same angular speed as the main body rolls around the longitudinal axis (roll speed), where the control device is arranged to determine the orientation of the longitudinal axis of the main body in relation to the external frame of reference with a frequency that is higher than the roll speed and adjust the thrust during a subsection of a complete revolution of the main body in relation to the external frame of reference in order to adjust the angle of attack, thereby adjusting the flight direction of the drone.

The present invention relates to a method of marking and identifying a target (110), and in particular, a method of using a Directed Energy Weapon (DEW) to heat a target without damaging it so that the target may be clearly identified by detectors and systems using thermally sensitive imaging.

A computer-implemented method for generating, while in flight, a feasibility indication indicating the feasibility of a weapon carried on the aircraft successfully engaging a target and / or the feasibility of a weapon carried on the target successfully engaging the aircraft, the method comprising the steps of providing a database describing a performance envelope of the weapon, identifying a best candidate polynomial from a plurality of candidate polynomials, using a generic algorithm to generate coefficients characteristic of that performance envelope, wherein the generic algorithm has a polynomial form, the polynomial variables being some or all of a group of firing condition parameters of the weapon or the aircraft, and transmitting the coefficients of the identified best candidate polynomial to the aircraft. 1. A method comprising: uploading a generic algorithm to a reconfigurator that includes a same generic algorithm; selecting, by an on-aircraft reconfigurator that includes the same generic algorithm, coefficients for the generic algorithm according to aircraft and target conditions; and generating, by the reconfigurator using the selected coefficients, a feasibility indication, wherein selecting, by an on-aircraft reconfigurator that includes the same generic algorithm, coefficients for the generic algorithm according to aircraft and target conditions comprises selecting, by an on-aircraft reconfigurator that includes the same generic algorithm, coefficients for the generic algorithm according to aircraft and target conditions if the aircraft and target are within the weapon's performance envelope.