Abstract: Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.

Abstract: A system for detecting threats using an overt threat detector, the system includes a computer-readable memory configured to store computer executable instructions; a processor configured to execute the computer executable instructions, the computer executable instructions comprising receiving historical data regarding vessel patterns in a geographic area; generating, using a computer processor, at least one overt threat model based on the received historical data; receiving tracking data of vessels currently in the geographic area; analyzing, using the computer processor, the tracking data of vessels using the at least one overt threat model; and modifying, using the computer processor, the tracking data of vessels based on the results of the analyzing step; and an output device configured to output the modified tracking data of vessels is disclosed.

Abstract: The system and method of projectile flight management using a combination of radio frequency orthogonal interferometry for the long range navigation and guidance of one or more projectiles and a short range navigation and guidance system to provide for more accurate targeting, especially in GPS-denied and GPS-limited environments.

Abstract: An aerodynamic nose cone capable of imaging through the nose cone is accomplished by forming the nose cone as an Afocal Axicon lens. Under a condition of RI?cos(X)/cos(3X) where RI is an effective refractive index and X is a cone half angle of the solid right-circular cone. EMR incident on a front portion of the cone undergoes a total internal reflection (TIR) and exits a trailing surface of the cone with approximately the same parallelism with which it entered the cone. EMR incident behind the front portion of the cone that exits the trailing surface with different parallelism than it entered may be directed to a light dump or through a frustum of a cone to re-establish the correct parallelism. The entire optical system may be monolithically integrated into the nose cone to eliminate alignment issues and moving parts.

Abstract: Seeker optics and a related method comprising: an objective for collecting and transmitting light from a target; at least one scattering surface; and a photo detector; wherein: the light transmitted from the objective at small off-boresight target angles propagates to and impinges upon the photo detector without impinging upon the scattering surface; the light transmitted from the objective at large off-boresight target angles propagates to, impinges upon and scatters upon the scattering surface; and the light scattered by the scattering surface propagates to and impinges upon the photo detector; whereby: the target may be detected and tracked at both small and large off-boresight angles, in a wide field of regard.

Abstract: An embodiment of a disaster response system is disclosed that includes a communication and monitoring environment (CME). The CME includes an incident command infrastructure, and a communication infrastructure configured to exchange data with the incident command infrastructure. The communication infrastructure includes a network comprising a plurality of sensor assemblies that are configured to wirelessly communicate with the communication infrastructure. The sensor assemblies are configured to acquire data that includes at least one of environmental conditions, motion, position, chemical detection, and medical information. One or more of the sensors are configured to aggregate data from a subset of the plurality of sensors. The CME is configured to detect an incident based on at least the data acquired by the sensor assemblies.

Abstract: An apparatus includes a detector and a light source configured to emit light. The apparatus further includes a disk with a set of prisms and that is configured to rotate, arranged to receive and direct the emitted light, and arranged to receive and direct backscattered light. The apparatus further includes a reflecting apparatus with multiple reflective facets and configured to rotate, arranged to reflect the emitted light, and arranged to reflect the backscattered light. A focusing apparatus is arranged to focus the backscattered light from the disk towards the detector.

Abstract: A guidance assembly and method for guiding an ordnance to a target. The assembly can operated in navigation and targeting modes and has an imager/seeker including an objective lens assembly and an imaging sensor array which provide image data for mapping and terminal seeker performance. The imager/seeker is pivotally mounted on the ordnance. An actuator is coupled to the imager/seeker and can be actuated to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position. A flight control unit communicates with the imager/seeker and the actuator, and has a processor which analyses the image data to provide navigation flight control signals for guiding the ordnance in the navigation mode of operation and determining a target direction via automatic target recognition or aimpoint algorithms for directing the ordnance to the target in the targeting mode of operation.

Abstract: A command control system includes an interception predicting section and an assigning section. The interception predicting section calculates a predicted intercept point of a target to be shot down and a guided missile to shoot down the target. The assigning section acquires first weather data of the predicted intercept point, and generates a launching instruction based on the first weather data so as to launch one of a first guided missile and a second guided missile as the guided missile. A method by which the first guided missile detects the target and a method by which the second guided missile detects the target are different.

Abstract: A method for occupancy map synchronization in multi-vehicle networks may include receiving three-dimensional perception sensor (3DPS) data. The method may include generating a data message including an occupancy map (OM) octree. The OM octree may be generated from an occupancy map constructed from the 3DPS data. The method may include reducing at least one of a messaging time or a messaging size of the data message including the OM octree. The method may include transmitting the data message including the OM octree via a leader vehicle controller communicatively coupled to a leader vehicle. The method may include receiving the data message comprising the OM octree via a follower vehicle controller communicatively coupled to the follower vehicle. The method may include generating a local occupancy map from the data message comprising the OM octree via the follower vehicle controller.

Abstract: Disclosed is a data reader and method of data reading for an imager with multiple fields of view, including directing a first field of view of the imager along a first path, directing a second field of view of the imager along a second path, and alternately selecting one of the first view or the second view via a view splitting/combining system comprising a rotating mechanism (e.g., a disk), disposed in the view path of the imager, the disk having reflective and transmissive/open portions. The system may include synchronization between rotation of the rotating disk and the imager, one synchronization comprises using a magnet on the rotating disk and a Hall sensor on a printed circuit board beside the rotating disk, the Hall sensor output then being used to synchronize image capture to motor position. Other synchronization methods are disclosed.

Abstract: A guidance system for a projectile having a mid-body. The guidance system having a mid-body semi-active laser seeker. The seeker has an objective lens assembly and a sensor array that reads laser energy and transmits data to determine the direction of the laser energy. A glint management unit is connected to mid-body in such a manner that glint laser energy is prevented from passing to the objective lens assembly and sensor array so as to enhance determination of the location of the target.

Abstract: Systems, apparatuses, and methods are described which provide a camera mount system. A camera mount is in communication with a positioning device. The positioning device has a compass, gyroscope, and emits an infrared light beam. The camera mount has a sensor that receives reflected and/or scattered infrared light from a moving target. The camera mount changes its orientation based on information from its sensor, and gyroscope and compass information from the positioning device.

Abstract: A monostatic, beaconless fiber transceiver for free-space optical links infers fine tracking information using receiver optoelectronics and an injected pointing dither (nutation). A MEMS steering mirror fine-points the beams and injects the nutation. While this may disturb fiber coupling and transmit beam pointing, link loss becomes negligible for sufficient SNR. The SNR for links without point-ahead correction is about 35 dB to keep dither loss below 0.1 dB and RMS spatial tracking noise below a tenth of the beam divergence. Since the pointing and tracking bandwidth is much smaller than the receiver communication bandwidth, this SNR is achievable with appropriate filtering. For point-ahead correction, a single-mode fiber transceiver can reach up to about 1 beamwidth of correction, while a few-mode fiber transceiver can reach up to about 1.75 beamwidths due to improved coupling sensitivity at higher point-ahead offsets.

Abstract: A hyperspectral analysis computer device is provided. The hyperspectral analysis computer device includes at least one processor in communication with at least one memory device. The hyperspectral analysis computer device is configured to store a plurality of spectral analysis data, receive at least one background item and at least one item to be detected from a user, generate one or more spectral bands for analysis based on the at least one background item, the at least one item to be detected, and the stored plurality of spectral analysis data, receive one or more mission parameters from the user, and determine a probability of success based on the one or more mission parameters and the generated one or more spectral bands.

Abstract: Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

Abstract: Apparatus and methods for coupling an optical beam from an optical source to a hi-tech system are described. A compact, low-cost beam-shaping and steering assembly may be located between the optical source and hi-tech system and provide automated adjustments to beam parameters such as beam position, beam rotation, and beam incident angles. The beam-shaping and steering assembly may be used to couple an elongated beam to a plurality of optical waveguides.

Abstract: A method includes showing a plurality of regions on a display each associated with a respective gimbal of a plurality of gimbals carried by a movable object and configured to depict data captured by a payload carried by the respective gimbal. The plurality of regions include a first region and a second region, and the plurality of gimbals include a first gimbal associated with the first region and a second gimbal associated with the second region. The method further includes, in response to a user interaction with the first region, controlling operation of the first gimbal and not operation of the second gimbal based on the user interaction with the first region when the movable object is operating in an independent mode, and simultaneously controlling the operation of the first gimbal and at least the operation of the second gimbal in a synchronized manner based on the user interaction with the first region when the movable object is operating in a simultaneous mode.

Abstract: A window assembly heat transfer system is disclosed in which a window member has a selected transparency to monitored or sensed light wavelengths. One or more passages are provided in the window member for flowing a single-phase or two-phase heat transfer fluid, the passages being optically non-transparent to the monitored or sensed light wavelengths. A mechanism allows either evaporation or condensation of the fluid and/or balancing of a flow of the fluid within the passages. In one embodiment, the window assembly can be made by producing passages in a top surface of a first single plate, optionally producing passages in a bottom surface of a second single plate and bonding the top surface of the first plate to a bottom surface of a second single plate to form the window member with the passage or passages. In another embodiment, the window assembly can be made by providing a core around which the window member material is grown and thereafter removing the core to produce the passage or passages.

Abstract: A method for simultaneous localization and mapping is provided, which can reliably handle strong rotation and fast motion. The method provided a simultaneous localization and mapping algorithm framework based on a key frame, which can support rapid local map extension. Under this framework, a new feature tracking method based on multiple homography matrices is provided, and this method is efficient and robust under strong rotation and fast motion. A camera orientation optimization framework based on a sliding window is further provided to increase motion constraint between successive frames with simulated or actual IMU data. Finally, a method for obtaining a real scale of a specific plane and scene is provided in such a manner that a virtual object is placed on a specific plane in real size.

Abstract: An optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.

Abstract: A window assembly heat transfer system is disclosed in which a window member has a selected transparency to monitored or sensed electromagnetic wavelengths. One or more passages are provided in the window member for flowing a single-phase or two-phase heat transfer fluid. A mechanism allows either evaporation or condensation of the fluid and/or balancing of a flow of the fluid within the passages. In one embodiment, the window assembly can be made by producing passages in a top surface of a first single plate, optionally producing passages in a bottom surface of a second single plate and bonding the top surface of the first plate to a bottom surface of a second single plate to form the window member with the passage or passages. In another embodiment, the window assembly can be made by providing a core around which the window member material is grown and thereafter removing the core to produce the passage or passages.

Abstract: The present disclosure provides an optical module comprising: a photoelectric conversion unit, a first demodulation circuit, and a second demodulation circuit; the first demodulation circuit and the second demodulation circuit are respectively connected to the photoelectric conversion unit; the photoelectric conversion unit is configured to convert the received optical signal into an electrical signal; the first demodulation circuit is configured to demodulate an electrical signal converted by the photoelectric conversion unit and generate a high-frequency electrical signal; the second demodulation circuit is configured to demodulate an electrical signal converted by the photoelectric conversion unit and generate a low-frequency electrical signal.

Abstract: A deployment body for a sensor array includes at least one superelastic spring formed of a shape memory alloy (SMA) material that enables activation of the deployment body. The SMA spring is configured to expand from a stowed position in which the SMA spring is wound around a central hub of the deployment body to a deployed position in which the SMA spring is extended in a radially outward direction relative to the central hub. A stiffness of the SMA spring enables the SMA spring to hold cables of the sensor array and maintain a deployed shape of the sensor array, which may be a volumetric array. Using the SMA material is advantageous in that the material is tuned to maintain superelasticity based on at least one of an intended operating temperature and a desired expansion ratio of stowed to deployed diameter of the deployment body.

Abstract: Disclosed is a method for compensating for disturbing couples for a movement simulator, the simulator including, for each axis, a monovariable correcting unit that receives a signal giving the difference between the setpoint ?rj and the measurement ?j for the corresponding axis and producing the control signal Uj. The disruptive couples are Coriolis, centrifugal and gravitational couples and furthermore a compensating law calculates a formula (a) estimating the disruptive couples, calculated on the basis of an error ?j(t) that is the control signal Uj filtered by a filter H(q?1), and the simulator is modelled with a dynamic model expressing the couples in an affine way with respect to a set of base parameters ? according to a matrix relationship of the type: formula (b), and a subset j of base parameters, the estimation of the couples being formula (c), and, online, the ?j are calculated via an iterative equation.

Abstract: Information encoded in an uplink beam (Lu) is transmitted from transceiver (10) on earth (1) to a communication satellite (20) in orbit. The uplink beam (Lu) travels through an atmosphere (2) there between, wherein a wavefront (Wu) of the uplink beam (Lu) is distorted as a result of its propagation through the atmosphere (2). The transceiver (10) comprises a wavefront sensor (12) to measure a reference distortion (Wr?) of a wavefront (Wr) of a reference beam (Lr). Adaptive optics (11) are used to pre-correct a wavefront (Wu) of the uplink beam (Lu) prior to its transmission based on the measured reference distortion (Wr?). The reference beam (Lr) originates from a guidestar satellite (30) formed by a separate man-made object at a distance (D) from the communication satellite (20) such that the reference beam (Lr) travels through the same part (2a) of the atmosphere (2) as the uplink beam (Lu).

Abstract: An information processing device is provided, for example, in a vehicle. A control unit of the information processing device executes flight control of an unmanned flying object such that the unmanned flying object moves to a destination and acquires a captured image from the unmanned flying object. The control unit performs adjustment of an arrival time at the destination, for example, depending on a congestion situation or movement guidance of the vehicle to an empty space at the destination on the basis of the captured image of the destination or a surrounding area of the destination. Further, retrieval of a movement route in the destination is performed on the basis of the captured image obtained by causing the unmanned flying object to move inside the destination and imaging the inside of the destination, and the detected movement route is set in a moving object which is used for movement in the destination.

Abstract: A sensing module includes a linear image sensor and an optical unit. The unit includes an optical element having a curved, outward surface and a covering on the outward surface. The covering has a slit formed therein. The optical unit faces the sensor with the slit perpendicular to a longitudinal axis of the sensor and images a wide field of view onto a single pixel of the linear sensor, wherein light impinging normal to the slit, at any location along the slit, is imaged on a central pixel of the sensor while light impinging one of a plurality of non-normal angles to the slit is imaged on an associated one of a plurality of non-central pixels of the sensor.

Abstract: Apparatuses, systems, and methods for producing an electromagnetic pulse (EMP). Charged-particle intercalated graphite is disposed at least partially around an explosive and both are positioned within a non-geomagnetic magnetic field. The non-geomagnetic magnetic field accelerates charged particles released by the detonation of the explosive. The non-geomagnetic magnetic field may be generated by permanent magnets. The explosive may be formed in a layer with the non-geomagnetic field being oriented perpendicular to the layer. The layer may be form in the shape of a disc. The explosive and the charged-particle intercalated graphite may be positioned within a resonant cavity that is configured to amplify one or more specific frequencies of electromagnetic energy.

Abstract: An antenna may include a base, a gimbal mount coupled to the base, and a first guide body coupled to the base and having a first guide slot. The antenna may include a second guide body rotatably coupled with respect to the base and having a second guide slot defining a steerable intersection position with respect to the first guide slot. The antenna may also have an antenna member coupled to the gimbal mount and extending through the steerable intersection position, and an actuator configured to selectively rotate the second guide body to steer the antenna member.

Abstract: A system and method for state estimation in spinning projectiles is provided. The state estimation is based, at least in part, on magnetic sensor data, angular velocity data, and correction terms applied to the magnetic sensor data and the angular velocity data. The system and method for state estimation in spinning projectiles estimates roll angles and roll rates of the spinning projectiles. The roll angle and roll rate estimates allow steering commands to be applied to steer the spinning projectiles in the proper direction.

Abstract: A munition includes a munition body containing explosive material. An electronic subsystem is active between release and detonation of the explosive material. One or more batteries are electrically connected to the electronic subsystem to provide power to the electronic subsystem prior to detonation. The one or more batteries are positioned adjacent to the explosive material to be accelerated outward as corresponding munition projectiles after detonation, increasing the effective payload of the munition by performing dual functions. In one or more embodiments, the explosive material is cylindrically shaped and longitudinally aligned in a warhead section of the munition body. The one or more batteries are annularly positioned on lateral surface of the explosive surface to form a cellular fragmenting structure. In a particular embodiments, the munition body is a missile body containing a rocket propulsion system and the electronic subsystem comprises a missile guidance system.

Abstract: A method is provided of generating a course-correction signal for a spin-stabilized projectile. The method includes capturing a time-sequence of images of a scene at a frame rate, comparing respective current images of the time-sequence of images to a corresponding previous image of the time-sequence of images, determining a rotation angle between the current and previous images, rotating the images using the rotation angle, identifying a target in the rotated images, generating target bearing angles to cause the projectile to correct its course toward the target using the target bearing angles, and adjusting the target bearing angles to compensate for the rotation of the images.

Abstract: A measuring arrangement having an optical transmitter and an optical receiver are disclosed. In an embodiment a measuring arrangement includes an optical transmitter configured to transmit electromagnetic measuring radiation into a transmission space, an optical receiver configured to receive measuring radiation reflected by an object in a reception space and a covering configured to reduce reception of an interference radiation by the receiver, wherein the interference radiation is measuring radiation not reflected by the object.

Abstract: A ball joint gimbal (BJG) seeker assembly is provided and includes a back shell, a retaining system disposed to urge the seeker ball toward the back shell and a piezoelectric ultrasonic motor and sensor system arrayed between the seeker ball and the back shell. The piezoelectric ultrasonic motor and sensor system is pre-loaded by the retaining system and configured to controllably drive an angular orientation of the seeker ball.

Abstract: Systems and methods are provided for performing alignment calibration of an RF antenna in satellite communications. Data is received that is representative of inertial navigation system and gimbal angle measurement signals. The received data is collected while a vehicle is operated in a reduced yaw motion and while the RF antenna is tracking a satellite. Equations are used that describe a mathematical relationship among the misalignments, offsets, and latency mismatch to the antenna gimbal control servo measurements. Estimates are generated for certain errors involved in the alignment process. The generated estimates are provided for pointing the RF antenna.

Abstract: A method for predicting arrival of a wind event at an aeromechanical structure includes sensing wind velocity in an atmospheric volume moving towards the aeromechanical structure to obtain a time series of spatially distributed wind velocity measurements, determining presence of the wind event from at least one of the distributed wind velocity measurements, and tracking the wind event based upon the time series of spatially distributed wind velocity measurements to estimate arrival time of the wind event at the aeromechanical structure. A wind-predicting system uses a lidar and a wind-predicting unit to implement this method. An aeromechanical apparatus integrates this wind-predicting system to predict wind events at the aeromechanical apparatus.

Abstract: Apparatus and associated methods relate to forming images for a terminal-imaging seeker using software defined optics. An optically-neutral lens with a ballistic-ogive-shaped front surface receives light from a scene aligned along an optical axis. The optically-neutral lens transmits the light received at the ballistic-ogive-shaped front surface to a planar rear surface, which is then transmitted to a coded-aperture plate aligned with the optical axis. The coded-aperture plate includes a plurality of pinhole-like apertures, each of which is configured to perform pinhole-like lensing of the scene. The plurality of pinhole-like apertures form a multiplex of overlapping images on a focal plane array aligned with the optical axis. An image processor reconstructs, based on a configuration of the plurality of pinhole-like apertures and the multiplex of overlapping images, a single image of the scene.

Abstract: A hyperspectral analysis computer device is provided. The hyperspectral analysis computer device includes at least one processor in communication with at least one memory device. The hyperspectral analysis computer device is configured to store a plurality of spectral analysis data, receive at least one background item and at least one item to be detected from a user, generate one or more spectral bands for analysis based on the at least one background item, the at least one item to be detected, and the stored plurality of spectral analysis data, receive one or more mission parameters from the user, and determine a probability of success based on the one or more mission parameters and the generated one or more spectral bands.

Abstract: Techniques for articulating a sunshield to shade portions of a spacecraft are disclosed. In one aspect, a spacecraft includes a body and an articulable sunshield. The spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin. The sunshield is configured to rotate about an axis substantially parallel to the pitch axis such that a selected location of an exterior portion of the body is shaded from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.

Abstract: A range finding system includes: an electromagnetic output to provide a first beam of electromagnetic radiation along a first beam path; an electromagnetic input to receive reflected electromagnetic radiation of the first beam from an object for determining a range of the range finding system from the object; and an enclosure including a side wall that surrounds a central axis of the enclosure, the side wall transparent to the electromagnetic radiation provided by the electromagnetic output. The electromagnetic output and electromagnetic input are disposed within the enclosure such that the electromagnetic input is located outside a second beam path of a second beam of electromagnetic radiation defined by a specular reflection of the first beam on the side wall. Since the electromagnetic input is located outside the second beam path, the specular reflection of the first beam off the side wall does not reach the electromagnetic input.

Abstract: A dual mode RF/IR seeker suitable for use in an anti-radiation missile is disclosed. The infrared sensor is responsive to radiation within the 4.0 to 4.8 micron band and the radio frequency sensor is responsive to radio frequency signals within a 6.5 to 16.5 GHz band. The infrared sensor comprises a folded Cassegrainian telescope arrangement, including a primary mirror which is transparent to radio frequency energy. The radio frequency sensor comprises an annular array of orthogonally disposed stripline flared notch radiating elements. A broadband microwave receiver, fabricated in a multilayered stripline package, is provided for forming radio frequency monopulse sum? (E) and difference (A) signals and for converting such radio frequency monopulse signals to suitable intermediate frequency signals for processing in an I.F. receiver.

Abstract: A torpedo apparatus comprises a propulsion module operable to propel the torpedo apparatus through water and a steering module operatively coupled to the propulsion module. The steering module including a plurality of fins which are controllable for controlling a direction of travel of the torpedo apparatus through water. A plurality of head modules are removably and interchangeably attachable to the torpedo apparatus, wherein each of the head modules houses at least one guidance assembly and at least one utility assembly. A power supply module is configured to provide power to the propulsion module, the steering module, and an attached one of the head modules.

Abstract: A sensing module includes a high speed, linear image sensor and an optical unit facing the sensor. The unit includes an optical element having a curved surface and a covering on an outward surface of the optical element. The covering has a slit formed therein. The optical unit images a wide field of view onto a single pixel of the linear sensor, wherein light impinging normal to the slit, at any location along the slit, is imaged on a central pixel of the linear sensor while light impinging at a non-normal angle to the slit, at any location along the slit, is imaged on a non-central pixel of the linear sensor.

Abstract: A method for reducing the low-frequency component of the measurement noise of a photosensitive imager and applications of same. The invention involves intentionally creating a non-straight scanning movement of the observed scene on the photosensitive matrix of the imager.

Abstract: A system for collision avoidance includes memory storing instructions which, when executed, cause one or more processors to perform determining a direction of flight of a first drone, causing broadcasting, in the direction of flight based, a beamformed signal of beacon frames, determining a new flight direction of the same first drone, in response to the new flight direction, causing broadcasting of the beacon frames in the new flight direction, detecting second beacon frames from a second drone associated with a direction from which the second beacon frames are arriving; in response, causing the first drone to perform, without input from a pilot, one or more of a change in elevation, heading, speed, or type of operation, directed toward causing the first drone to follow a flight path that is separated from the second drone.

Abstract: An object detection system for a marine vessel having at least one marine drive includes at least one image sensor positioned on the marine vessel and configured to capture an image of a marine environment on or around the marine vessel, and a processor. The object detection system further includes an image scanning module executable on the processor that receives the image as input. The image scanning module includes an artificial neural network trained to detect patterns within the image of the marine environment associated with one or more predefined objects, and to output detection information regarding a presence or absence of the one or more predefined objects within the image of the marine environment.

Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

Abstract: Embodiments of the disclosure provide an encapsulated compressor overload, an encapsulated compressor relay start, an encapsulated head pressure control switch and a wiring diagram for a circuit for air conditioning units which prevent gases from being ignited by means of encapsulating sparking components, use of solid-state switching devices, and/or wiring circuits in such a way that open contacts do not contain enough energy to produce a spark capable of igniting the atmosphere.

Abstract: A multi-axis motor includes a first elongate magnet member disposed in a first orientation and a second elongate magnet member disposed in a second orientation orthogonal to the first orientation and mechanically coupled to the first elongate magnet member. The first elongate magnet member is operable to adjust a first axis of a fine axis structure. The second elongate magnet member is operable to adjust a second axis of the fine axis structure.