31results about "Direction controllers" patented technology

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.

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.

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.

A computer-implemented method of training a machine learning, ML algorithm to control spin-stabilized steerable projectiles is described. The method comprises: obtaining training data including respective policies and corresponding trajectories of a set of spin-stabilized steerable projectiles including a first projectile, wherein each policy relates to steering a projectile of the set thereof towards a target and wherein each corresponding trajectory comprises a series of states in a state space of the projectile (S2001); and training the ML algorithm comprising determining relationships between the respective policies and corresponding trajectories of the projectiles of the set thereof based on respective results of comparing the trajectories and the targets (S2002).

An MGS battery system which is designed as a drop in substitute for the existing MGS battery pack in an FCS for use with a TOW platform. The MGS battery system provides for a single integrated power source which can provide for electrical power to a variety of different output ports that each have different supply requirements. The MGS battery system takes in multiple inputs to supply the power to charge onboard batteries. The MGS battery system can handle the multiple inputs and the multiple outputs while only utilizing a single power conversion stage for each electrical path.

A computer-implemented method for controlling a combat system, the method comprising: determining one or more combat assets included in the combat system, each combat asset being configurable to engage one or more target objects; receiving sensor data indicating a position, and preferably movement, of one or more target objects relative to the one or more combat assets; simultaneously determining, by an agent component and based on the received sensor data, an action command for each of the one or more combat assets and a zero-op command to instruct at least one, preferably a subset, of the combat assets not to engage any target object during a specified time interval;and transmitting the respective action command to the one or more combat assets, wherein the agent component preferably comprises a machine learning algorithm, more preferably a machine learning algorithm based on reinforcement learning.

Test device (20) for military equipment (10), comprising: at least one test component (22) for testing an electronic component (12) of the military equipment (10) and a test controller (24) for operating the at least one test component (22), wherein the test controller (24) - has at least one hardware-neutral communication interface (25) for data communication with an operator device (30), - for data communication with the operating device (30) has a web server (26) connected to at least one communication interface (25) and - for operating at least one test component (22) integrated into the electronic component (12) of the military equipment (10).

An MGS battery system which is designed as a drop in substitute for the existing MGS battery pack in an FCS for use with a TOW platform. The MGS battery system provides for a single integrated power source which can provide for electrical power to a variety of different output ports that each have different supply requirements. The MGS battery system takes in multiple inputs to supply the power to charge onboard batteries. The MGS battery system can handle the multiple inputs and the multiple outputs while only utilizing a single power conversion stage for each electrical path.

A wedged window (108) for a multi-mode system (102) includes an outer curved surface (310) and an inner curved surface (308). The inner curved surface (308) is tilted at a specified angle with respect to the outer curved surface (310). The outer curved surface (310) is configured to receive a signal wavefront (110) for a multi-mode optical device (100) that includes the multi-mode system (108) and an off-axis optical system (104). The inner curved surface (308) is configured to direct a refracted wavefront (208) based on the signal wavefront (110) toward the off-axis optical system (104).

The invention relates to a sensing device (1) for a missile, in particular a guided missile, comprising an optical system (2) which is designed to image radiation (5, 6) onto a detector plane (3) of a detector device (4) of the sensing device (1) in at least one spot (7, 8), wherein the sensing device (1) comprises a phase element (9) which is designed to produce a blur of the at least one spot (7, 8) in the detector plane (3), wherein a control unit (10) is designed to transform, by means of a transformation algorithm, in particular based on artificial intelligence, the at least one spot (7, 8), which is imaged in a blurred manner in the detector plane (3) and has a first image sharpness, into at least one spot having a second image sharpness greater than the first image sharpness.

A data recorder is in operative communication with a sensor. The data recorder records both data that is internal to the data recorder and external to the data recorder. The data that is external to the data recorder includes a state status of the sensor. The data that is external to the data recorder is merged into a data stream with the data that is internal to the recorder. The data recorder enables the determination of, amongst other things, whether an Electronic Thermal Battery Initiator (ETBI) initiated its firing pin after detecting a valid launch condition of a test projectile within a required time frame. The timing data from the data record assembly can be verified to ensure that the ETBI has properly initiated. The test projectile may be a modular projectile to allow easy modular installation of the data recorder as a modular component of the test projectile.

A projectile 1 carries a thermal or infrared (IR0 beacon B which is tracked using an infrared imager 3. The imager scans an image of a scene including the beacon and a target 2 in raster fashion havin

A wedged window for a multi-mode system includes an outer curved surface and an inner curved surface. The inner curved surface is tilted at a specified angle with respect to the outer curved surface. The outer curved surface is configured to receive a signal wavefront for a multi-mode optical device that includes the multi-mode system and an off-axis optical system. The inner curved surface is configured to direct a refracted wavefront based on the signal wavefront toward the off-axis optical system.

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.

Inertial sensor system (IMU) for use in an inertial navigation system of a missile (30), comprising: a first inertial sensor module (B1) comprising at least two first inertial sensors (C1, ..., Ci) of a first inertial sensor type and a first, multiplexer (MUX1) coupled with the outputs of the first inertial sensors (C1, ..., Ci); a second inertial sensor module (B2) comprising at least one second inertial sensor (D1, ..., Dj) of a second inertial sensor type different from the first inertial sensor type; and a control processor (P) which is coupled to the first multiplexer (MUX1) and which is designed to control the first multiplexer (MUX1) to output the sensor measurement values ​​of an inertial sensor selected by the control processor (P) from the first inertial sensors (C1, ..., Ci), wherein the control processor (P) is further designed to select an inertial sensor of the first inertial sensors (C1, ..., Ci) and an inertial sensor of the second inertial sensors (D1, ..., Dj) depending on an instantaneous flight phase of the missile (30).

Methods, systems, and apparatus, including computer programs encoded on a storage device, for guiding weapon systems to targets are disclosed. A method includes obtaining sensor data from one or more sensors mounted to a weapon system; providing the sensor data as input to a target model, the target model being an artificial intelligence model trained to detect a particular type of object within a set of sensor data from one or more particular types of sensors and to provide output that is decipherable by flight control systems to control navigation operations; obtaining output data from the target model; providing the output data from the target model to a flight control system of the weapon system; and controlling operation of one or more control surfaces of the weapon system, responsive to the output data to control a trajectory of the weapon system.

The present invention relates to a method (M) for controlling vehicles (120), in particular flying vehicles, and convoys of such vehicles. A mission specification (3) with further information is transmitted to a control unit (100) implemented in a vehicle (120). The control unit (100) networks with other vehicles (120) mentioned in the mission specification (3), each with corresponding additional control units (100). An OODA loop algorithm (1) implemented in the control unit (100) is started and executed for optimal mission objective achievement, taking into account the acquired sensor data and the transmitted sensor data of all other interconnected control units (100) of vehicles (120) listed in the participant list (4), so that subsequent control of the vehicles (120) takes place based on the results process of this algorithm.These final procedural steps are repeated until the mission objective (2) is achieved. In addition, a corresponding control unit (100), a system (110), and a vehicle (120) are disclosed.

A system and method for measurement and correction of aero-optical and aero-thermal effects to an EO / IR sensor's window / dome on a supersonic flight-vehicle. Range-gating of laser pulses measures and separates aerodynamic and atmospheric effects. Separate control algorithms and control loops at different update rates both simplifies the control algorithms and improves overall performance. The use of a MEMS MMA having tip / tilt / piston capabilities as the deformable mirror to provide wavefront correction enhances overall performance. The corrected laser pulses may also be used to actively illuminate a target to provide both active and passive detection.

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

This laser beam measurement system comprises a laser source configured to emit laser radiation towards a target and a detector (2) arranged to receive said reflected laser radiation (8) from the target, which is equipped with a pixel array (10) and configured to measure the location of said reflected laser radiation (8) on the pixel array (10). The laser beam measurement system further comprises a diapometer (4) equipped with first and second optical components (4A, 4B) arranged along the optical path of said reflected laser radiation (8) and which are free to rotate independently of each other about an optical axis (A) of the laser beam measurement system. The first and second optical components (4A, 4B) are each equipped with a metasurface (12A, 12B) configured to deflect said reflected laser radiation at first and second deflection angles (α1, α2), respectively. (See Figure 2 for abbreviations.)

In accordance with at least one aspect of this disclosure, a lens is provided. The lens can be used in an imaging platform of a moving platform (e.g., a projectile or guided munition), for example, in a seeker arrangement. The lens can be configured to optical rotation information of the moving platform to an optical sensor as the moving platform moves in space, for example, following a mission profile.

A laser-guided decoy system and method, the system comprising first and second functional units, the first functional unit being a combination of laser warning, information processing and command modules, and the second functional unit being a combination of a laser and a decoy head, which are arranged so that the first functional unit detects and processes laser-guided target indication signals, forms commands and transmits the commands to the second functional unit, and the second functional unit emits and scatters laser decoy jamming light in accordance with the commands, wherein the decoy head in the second functional unit comprises a laser scatterer, a base and a laser connection part, the laser scatterer is composed and combined with the base and the laser connection part so that the laser decoy jamming light emitted by the laser in the second functional unit in accordance with the commands can irradiate into the decoy head and scatter the laser, and the scattered laser presents a strong laser energy field in an air space with a pitch ≥-30° to ≤95° and an azimuth >0° to ≤360°.

A computer-implemented method of controlling an engagement system, the method comprising: determining one or more engagement means comprised in the engagement system, wherein each of the engagement means is configurable to engage one or more targets; receiving sensor data indicative of a position, and preferably movement, of the one or more targets relative to the one or more engagement means; simultaneously determining, by an agent component and based on the received sensor data, an action command for each of the one or more engagement means and a no-operation command instructing at least one, preferably a subset of, the engagement means to not engage any target during a specified time interval; and transmitting the respective action command to the one or more engagement means, wherein the agent component preferably comprises a machine-learning algorithm, more preferably a reinforcement learning based machine-learning algorithm.

Detection device (1) for a missile, in particular a guided missile, comprising an optical device (2) configured to image radiation (5, 6) onto a detector plane (3) of a detector device (4) of the detection device (1) into at least one spot (7, 8), wherein the detection device (1) has a phase element (9) configured to generate a blur of the at least one spot (7, 8) in the detector plane (3), wherein a control device (10) is configured to transform the at least one blurred spot (7, 8) imaged in the detector plane (3) and having a first image sharpness into at least one second image sharpness with greater image sharpness than the first image sharpness by means of a transformation algorithm, in particular based on artificial intelligence.

An optics system includes a convex catching mirror located within respect to the concave primary mirror to form an optical path for a field of view. A conical volume is formed with respect to the concave primary mirror and the convex catching mirror, the optical path not obstructed by the conical volume. A component within the conical volume.