448results about "Direction controllers" patented technology

A guidance system for a guided munition has an inertial measurement unit (IMU) or another type of first sensor on the guided munition, electro-optical / infrared (EO / IR) sensor on the guided munition, and a guidance computer assembly (GCA) having a Programmable Real-Time Unit Industrial Communication SubSystem (PRU-ICSS), wherein the PRU-ICSS is in operative communication with the IMU or another type of first sensor and the EO / IR. The PRU-ICSS has a first Programmable Real-Time Unit (PRU), wherein the first PRU is programmed to receive and process input data from the IMU or another type of first sensor on the guided munition, and the PRU-ICSS has a second PRU, wherein the second PRU is programmed to receive and process input data from the EO / IR sensor on the guided munition.

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 system comprises a plurality of sensor systems, a counter drone, and a processor. A sensor system of the plurality of sensor systems comprises one or more sensors that are connected to a network. The counter drone is connected to the network. The processor is configured to receive an indication of a potential target from the plurality of sensor systems; generate a fused data set for the potential target, determine whether the potential target comprises the threat drone based at least in part on the fused data set; and in response to determining that the potential target comprises the threat drone, provide counter drone instructions to the counter drone.

A multispectral image capture device includes an imaging platform having arranged thereon an image sensor comprising a photosensitive surface and an optical unit, a gimbals system for controlling a line of sight of the image sensor, a filter wheel comprising a series of n spectral filters arranged between the image sensor and an imaging target; and a drive system configured to rotate the filter wheel at a constant velocity so as to bring each of the spectral filters into a line of sight between the image sensor and the imaging target. A controller is adapted to synchronize movement of the imaging platform, control of line of sight of the image sensor with the gimbals, and constant rotation of the filter wheel, such that the image sensor captures a sequence of overlapping step-and-stare images through the series of rotating spectral filters without changing a speed of rotation of the filter wheel.

A ceramic substrate including a porous internal structure including a sealant infiltrator. The sealant infiltrator includes sodium and silicate. The sealant infiltrator infiltrates at least some of the plurality of pores and closes the plurality of pores filled with the sealant infiltrator when exposed to a negative pressure. The sealant infiltrator is distributed across the exterior surface of the ceramic substrate.

The invention provides a system for precise targeting in GPS-denied environments using a plurality of Computer-Readable Image Markers (CRIMs) and imaging devices. CRIMs, such as Apriltags, are deployed around a target area by an aerial vehicle. Each CRIM includes a unique code and an anchor that absorbs moisture to stabilize its position. High-altitude imaging devices capture the CRIMs' positions relative to the target, and this data is processed to create a map for autonomous navigation. An attack drone uses this map, identifying unmoved CRIMs to adjust its course and engage the target accurately, even in contested environments with electronic countermeasures. The method leverages robust image recognition, reducing computational load and enhancing reliability. The system offers a cost-effective solution for military and humanitarian applications where GPS is compromised.

A guidance system for a guided munition has an inertial measurement unit (IMU) or another type of first sensor on the guided munition, electro-optical / infrared (EO / IR) sensor on the guided munition, and a guidance computer assembly (GCA) having a Programmable Real-Time Unit Industrial Communication SubSystem (PRU-ICSS), wherein the PRU-ICSS is in operative communication with the IMU or another type of first sensor and the EO / IR. The PRU-ICSS has a first Programmable Real-Time Unit (PRU), wherein the first PRU is programmed to receive and process input data from the IMU or another type of first sensor on the guided munition, and the PRU-ICSS has a second PRU, wherein the second PRU is programmed to receive and process input data from the EO / IR sensor on the guided munition.

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 flying vehicle is disclosed with a plurality of projectile systems that each contains a projectile for projecting at another flying device. The flying vehicle can include a control system, a flight system in communication with the control system for enabling the flying vehicle to fly, a first projectile system in communication with the control system and a second projectile system in communication with the control system. The control system determines, based on a characteristic of a target flying vehicle, whether to implement a first mode utilizing the first projectile system or a second mode utilizing the second projectile system to capture the target flying vehicle.

A dual-mode roll / nod gimballed seeker is configured to provide an unobstructed path for a forming-warhead penetrator. A nod assembly includes first and second seekers separately offset from the roll axis whose FOV overlap within a stand-off range to a target. A roll gimbal rotates the dome and nod assembly around the roll axis. A nod gimbal rotates the nod assembly about a nod axis over a nod FOR that causes the seekers to cross the roll axis and obstruct a path along the roll axis. At terminal, the nod gimbal rotates the nod assembly to a nominal nod angle at which the path is unobstructed to detonate the forming warhead and project a penetrator along the path through the dome. This alleviates the need for a precursor charge and saves precious volume in the airframe, which is of particular import for small diameter warheads, in particular those having a diameter of no more than 8 inches.

The system comprises a plurality of sensor systems, a counter drone, and a processor. A sensor system of the plurality of sensor systems comprises one or more sensors that are connected to a network. The counter drone is connected to the network. The processor is configured to receive an indication of a potential target from the plurality of sensor systems; generate a fused data set for the potential target, determine whether the potential target comprises the threat drone based at least in part on the fused data set; and in response to determining that the potential target comprises the threat drone, provide counter drone instructions to the counter drone.

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 closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and / or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

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.

The invention relates to an automatic axis calibration method, device and equipment for a photoelectric tracking and aiming system, and the method comprises the steps: controlling an imaging load to be locked, carrying out the offset tracking and scanning of a target, starting laser ranging, carrying out the real-time statistics of a laser echo rate corresponding to each offset value, and carrying out the calculation of an offset value; determining a corresponding offset value when the laser echo rate reaches the highest; wherein the corresponding offset value when the laser echo rate reaches the highest value is the parallelism deviation value of the optical axis of the imaging load and the optical axis of the laser; the optical axis of the imaging load is corrected on the basis of the offset value when the laser echo rate reaches the highest, so that the optical axis of the imaging load is parallel to the optical axis of the laser. According to the method, specific precise axis calibration equipment does not need to be additionally arranged outside the photoelectric tracking and aiming system, an axis calibration device does not need to be designed in the photoelectric tracking and aiming system, the existing hardware structure of the photoelectric tracking and aiming system is directly controlled through software, and the technical problem of high cost in related technologies is solved.

The invention discloses an infrared radiation simulation device which comprises a radiation cabin, an infrared radiation device is arranged in the radiation cabin, the infrared radiation device comprises an infrared radiation body and a reflection device, and the reflection device is arranged on the side, emitting infrared radiation, of the infrared radiation body and used for generating and enhancing the infrared radiation; and the battery cabin is internally provided with a control circuit and a battery, the control circuit controls the infrared radiation device to emit radiation through a pulse modulation technology, and the battery is used for providing electric energy for the infrared radiation device. The infrared radiation simulation device provided by the invention can meet low-cost and reliable observation of a space-based infrared guidance detection system.

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.

The invention relates to the technical field of cannonball outer trajectory measurement, in particular to an outer trajectory parameter measuring device and method based on an electric field sensor array. The system comprises a detection array composed of four electric field sensors. The method comprises the following steps: according to an electric field intensity change rate detected by an electric field sensor when a charged projectile flies nearby the electric field sensor, establishing each parameter relational expression by combining a Coulomb law; and carrying out indirect measurement on the position and the speed of the charged projectile according to the calibration and speed calibration equation. According to the invention, the electric field sensor is used for non-contact measurement of outer ballistic parameters based on the electrostatic detection technology, no interference is caused to the projectile, the cost is low, and the operation is simple; the device is high in adaptability, can be suitable for various different measurement environments, and is wide in application range.

To relatively increase tracking accuracy of a target even when the number of motion models in a filter having the plurality of motion models is limited in a tracking device.SOLUTION: A tracking device 10 includes a model selection unit 15 and a smoothing unit 12. The model selection unit 15 determines whether an object parameter is set as a selection parameter on the basis of a difference between a current value corresponding to an observed value of a target at current object time and a previous value corresponding to a result of predicting at least one of a position and a route of the target at the current object time at previous object time. The smoothing unit 12 sets an object parameter as a parameter of a motion model corresponding to the object parameter when the object parameter is set as the selection parameter in a case of predicting at least one of the position and the route of the target at the next object time using the observed value of the target at the current object time, and sets the current value as a state amount estimated by the filter when the object parameter is not set as the selection parameter.SELECTED DRAWING: Figure 1

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 method for guiding an interceptor missile (50) to an approaching aircraft (30), in which a reconnaissance missile (2) is launched and brought into an IR-transparent atmospheric layer (45), where it tracks the aircraft (30) with an IR sensor (10) and transmits tracking data of the aircraft (30), and the interceptor missile (50) is guided to the aircraft (30) using this tracking data. To enable a rapid and precise guidance of an interceptor missile (50) to an approaching hypersonic aircraft, it is proposed that the reconnaissance missile (2) be rocket-powered and track the aircraft (30) with its launch rocket engine (24) extinguished.

A missile system includes a sight having a targeting image sensor for obtaining a reference image and receiving an input defining a desired point of impact, and a missile. The missile has a seeker image sensor having an iFOV that is at least three times wider in each dimension than an iFOV of the targeting image sensor. A processing system of the missile receives the reference image, receives sampled images from the seeker image sensor during flight, and performs image registration between the reference image and the sampled image. The image registration includes down-sampling of the reference image so as to match a resolution of the sampled images. The image registration is used to determine the desired point of impact within the sampled images, and the missile is steered towards the desired point of impact.

A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and / or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de- spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and / or emitter system is configured for receiving and / or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.