Abstract: A computer-implemented method performed by a centralized coordinated vehicle guidance system may include: obtaining analytics data for a plurality of vehicles or objects centrally communicating with or detected by the centralized coordinated vehicle guidance system; detecting, based on the analytics data, a predicted collision event involving multiple pairs of the plurality of vehicles or objects; determining trajectory adjustment information for a first vehicle of the plurality of vehicles involved in the collision event; and outputting the trajectory adjustment information to cause the first vehicle to modify its trajectory.

Abstract: A video processing system includes: an object movement information acquiring means for detecting a moving object moving in a plurality of segment regions from video data obtained by shooting a monitoring target area, and acquiring movement segment region information as object movement information, the movement segment region information representing segment regions where the detected moving object has moved; an object movement information and video data storing means for storing the object movement information in association with the video data corresponding to the object movement information; a retrieval condition inputting means for inputting a sequence of the segment regions as a retrieval condition; and a video data retrieving means for retrieving the object movement information in accordance with the retrieval condition and outputting video data stored in association with the retrieved object movement information, the object movement information being stored by the object movement information and video d

Abstract: [A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising: roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

Abstract: Various embodiments associated with a composite image are described. In one embodiment, a handheld device comprises a launch component configured to cause a launch of a projectile. The projectile is configured to capture a plurality of images. Individual images of the plurality of images are of different segments of an area. The system also comprises an image stitch component configured to stitch the plurality of images into a composite image. The composite image is of a higher resolution than a resolution of individual images of the plurality of images.

Abstract: When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle ?0i of a start time and a gimbal angle ?ci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle ?ci of the fixed interval and a gimbal angle ?fi of a completion time of the attitude change. The obtained ?0i, ?ci, ?fi and an attitude change period ? are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.

Abstract: The present invention relates to the control of munitions, missiles and projectiles, in flight. The present invention further relates to systems and methods for control of munitions, missiles and projectiles in flight with the use of activatable or deployable flow effectors that remain stowed or inactive during launch or firing, and can be actuated after launch or firing on demand. More specifically, the present invention relates to systems and methods for control of munitions, missiles, and projectiles by activating and/or deactivating a control actuation system (CAS) based on measurements of an inertial measurement unit (IMU) and sensors integrated into such IMU, the IMU and sensors being at least part of a configurable guidance sensor suite (CGSS).

Abstract: 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.

Abstract: The present invention relates to systems and methods for providing location and guidance, and more particularly for providing location and guidance in environments where global position systems (GPS) are unavailable or unreliable (GPS denied and/or degraded environments). The present invention further relates to systems and methods for using inertial measurement units IMUs to provide location and guidance. More particularly, the present invention relates to the use of a series of low-accuracy or low-resolution IMUs, in combination, to provide high-accuracy or high-resolution location and guidance results. The present invention further relates to an electronics-control system for handing off control of the measurement and guidance of a body in flight between groups or subgroups of IMUs to alternate between high dynamic range/lower resolution and lower dynamic range/higher resolution measurement and guidance as the environment dictates.

Abstract: Using a distance sensor, a set of distances to a target object is measured, a distance in the set being measured at a time. From the set of distances and corresponding times, a trajectory of the target object is predicted. Based on receiving a signal identifying a friendly device, a correlation of the trajectory with a trajectory of the friendly device is determined. Responsive to the trajectory being predicted to intercept a defined volume around the distance sensor and responsive to the correlation being above a threshold degree of correlation, the target object is classified as a threat. Responsive to the trajectory being predicted to intercept a defined volume around the distance sensor and responsive to the correlation being below a threshold degree of correlation, a threat level corresponding to the target object is identified based on the trajectory of the target object and trajectory of the friendly device.

Abstract: A method for detecting a radionuclide using energy spectrum data represented by a count depending on energy obtained from a radiation detector, including: calculating a count ratio for a particular energy value using a background energy spectrum data measured without a target object to detect the radionuclide and a target energy spectrum measured in the presence of the target object; and comparing a background count ratio and a target object count ratio, where the count ratio is a ratio of a low count sum of count values which is an energy value or less divided by a high count sum of the count values which is greater than the particular energy value, or a ratio of the low count sum of the count values which is smaller than the particular energy value divided by the high count sum of the count values which is the particular energy value or greater.

Abstract: A nose assembly of an aircraft includes a nose airframe having a nonhorizontal mounting surface and a turret assembly mounted on the nonhorizontal mounting surface. The turret assembly includes a turret device housing rotatable relative to the nonhorizontal mounting surface. The nose airframe includes a nose skin forming a nose fairing having an apex aperture. The nose skin at least partially covers the turret assembly such that the turret assembly is at least partially inset in the apex aperture of the nose fairing.

Abstract: A method and system for nonlinear trajectory shaping guidance law capable of providing a robust guidance solution suitable for multi-mission, multi-mode operations. The nonlinear trajectory shaping guidance law offers (1) a dual layered GL gains calculation: (i) NTS time varying adjustment accounting for engine on/off and L/D variation and (ii) general explicit guidance algorithm based sub-optimal fixed-gain selection while still maintaining its trajectory shaping capability for short range to go missions; (2) flight path angle (FPA) command tracking and following to ensure a high probability of target destruction while minimizing collateral damages; (3) high precision impact point calculation factoring in target location errors or motion and maneuvering uncertainties; and (4) heading error angle minimization.

Abstract: In one aspect, an example method includes a processor (1) applying a feature map network to an image to create a feature map comprising a grid of vectors characterizing at least one feature in the image and (2) applying a probability map network to the feature map to create a probability map assigning a probability to the at least one feature in the image, where the assigned probability corresponds to a likelihood that the at least one feature is an overlay. The method further includes the processor determining that the probability exceeds a threshold, and responsive to the processor determining that the probability exceeds the threshold, performing a processing action associated with the at least one feature.

Abstract: A modular fuselage for an unmanned aerial vehicle (UAV) includes a battery module, an avionics module, and a mission payload module. The battery module houses a battery to power the UAV. The avionics module houses flight control circuitry of the UAV. The mission payload module houses equipment associated with a mission of the UAV. The battery module, the avionics module, and the mission payload module are detachable from each other and mechanically securable to each other to contiguously form at least a portion of the modular fuselage of the UAV.

Abstract: Embodiments herein describe tracking the location and orientation of a target in a digital image. In an embodiment, this tracking can be used to control navigation for a vehicle. In an embodiment, a digital image can be captured by a visual sensor is received. A first array including a plurality of binary values related to the pixel velocity of a first plurality of pixels in the digital image as compared to corresponding pixels in a first one or more prior digital images can be generated. A second array including a plurality of values related to the standard deviation of pixel intensity of the first plurality of pixels in the digital image as compared to corresponding pixels in a second one or more prior digital images can be further generated. A plurality of thresholds relating to the values in the second array can be determined.

Abstract: A computer implemented system and method of tracking objects and motion in video using techniques for agile switching between a number of tracking techniques, detecting and analyzing periodic motion, and using regular expression techniques for identifying patterns.

Abstract: A method of creating a dynamically sharp location based filter includes: placing a moving object containing two or more antennas used for direction finding of a radiation source within a anechoic testing chamber; moving one or more radio transmitters within the anechoic chamber relative to a future spatial location, angle, and/or position of the moving object over a defined time; record an expected angle of arrival of one or more signals of the one or more radio transmitters with respect to the future spatial location, angle, and/or position of the moving object over the defined time; and program a filter within the moving object based on the recorded expected angle of arrival of the one or more signals.

Abstract: A flight-path determination device for determining a flight path of a flying object has a position determination apparatus to detect a position of the flying object, an alignment apparatus that to verify whether the position of the flying object is within one specified approach path of a number of specified approach paths, and a path determination apparatus to output the relevant approach path as the flight path of the flying object if the position of the flying object is within one of the specified approach paths.

Abstract: A method and a device for providing a dummy target via decoy chaffs for protecting a vehicle and/or an object from radar-guided missiles. After identification of the radar-guided missile and calculation of a decoy chaff pattern, the decoy chaff pattern is presented in the form of polar coordinates in accordance with the firing of shots, a “cut-off” distance for the determination of a defence radius is then found in these polar coordinates. A minimum distance between the disassembly or detonation points within the defence radius is set. The dummy target is then optimized on the basis of the “cut-off” distance and the minimum distance between the disassembly or detonation points. As a result of this calculation, the only decoy chaffs that are deloyed are those that meet the conditions, i.e. that have a minimum distance between the disassembly or detonation points within the defence radius in the optimized dummy target.

Abstract: A multivariate path-based anomaly detection and prediction service (“anomaly detector”) can generate a prediction event for consumption by the APM manager that indicates a likelihood of an anomaly occurring based on path analysis of multivariate values after topology-based feature selection. To predict that a set of metrics will travel to a cluster that represents anomalous application behavior, the anomaly detector analyzes a set of multivariate date slices that are not within a cluster to determine whether dimensionally reduced representations of the set of multivariate data slices fit a path as described by a function.

Abstract: An inertial measurement system comprising: a first, roll gyro with an axis oriented substantially parallel to the spin axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros; operate a Kalman filter that receives a plurality of measurement inputs including at least roll angle, pitch angle and yaw angle and that outputs at least a roll angle error; initialise the Kalman filter with a roll angle error uncertainty representative of a substantially unknown roll angle; generate at least one pseudo-measurement from stored expected flight data; provide said pseudo-measurement(s) to the corresponding measurement input of the Kalman filter; and apply the roll angle error from the Kalman filter as a correction to the roll angle.

Abstract: In one embodiment, a method implemented on an access point of a wireless communication system includes: determining an estimate for a relative velocity between a mobile wireless client device and the access point, the mobile wireless client device communicating wirelessly with the access point over a channel; determining a channel coherence time for the channel using said estimated relative velocity; and determining a maximum aggregated frame size based on the determined channel coherence time.

Abstract: An inertial measurement system for a spinning projectile comprising: first (roll), second and third gyros with axes arranged such that they define a three dimensional coordinate system; at least a first linear accelerometer; a controller, arranged to: compute a current projectile attitude comprising a roll angle, a pitch angle and a yaw angle; compute a current velocity vector from the accelerometer; combine a magnitude of said velocity vector with an expected direction for said vector to form a pseudo-velocity vector; provide the velocity vector and the pseudo-velocity vector to a Kalman filter that outputs a roll gyro scale factor error calculated as a function of the difference between the velocity vector and the pseudo-velocity vector; and apply the roll gyro scale factor error from the Kalman filter as a correction to the output of the roll gyro.

Abstract: According to an embodiment of the present invention, an apparatus for controlling a moving object includes a trajectory control unit configured to control a trajectory of the moving object and a position control unit configured to control a position of the moving object. Thus, it is possible to control an angle at which the moving object enters a target point.

Abstract: The system and method for accurately determining range-to-go for the time-delayed command detonation of a projectile. Using dual laser and/or radio frequency detectors on a spinning projectile to determine the range-to-go, time-to-go, or lateral offset from the projectile to the target. The detectors are forward facing and rear facing and are located in a tail kit such that cost can be greatly reduced on a spinning projectile. The deployable detector(s) may be a light pipe, mirrors, or the like and comprise APD or PIN diodes.

Abstract: Disclosed are systems, devices, and methods for controlling an aerial vehicle. An exemplary method may include receiving data indicating a location and an altitude of the aerial vehicle, receiving data indicating a destination of the aerial vehicle, determining a vector from the location of the aerial vehicle to the destination of the aerial vehicle, receiving prevailing wind pattern data regarding winds at the location and altitude of the aerial vehicle, planning a path for the aerial vehicle to move along the vector based on the prevailing wind pattern data, and causing the aerial vehicle to adjust the altitude of the aerial vehicle based on the prevailing wind pattern data and the planned path.

Abstract: Systems for landing and facilitating power flow or data transfer between an unmanned aerial vehicle (UAV) and a charging mat using a boom are described. The system includes a mat with a conductive mesh on the top and a conductive surface on the other bottom of the mat. The conductive mesh and bottom conductive surface are separated (electrically isolated) by an isolation core. The outer portion of the boom contacts part of the conductive mesh of the mat to create an electrical pathway. An inner portion of the boom penetrates through the top layer conductive mesh, through the isolating core, and contacts the bottom conductive surface of the mat to create another electrical pathway.

Abstract: The present subject matter relates to systems, devices, and methods for data-driven precision agriculture through close-range remote sensing with a versatile imaging system. This imaging system can be deployed onboard low-flying unmanned aerial vehicles (UAVs) and/or carried by human scouts. Additionally, the present technology stack can include methods for extracting actionable intelligence from the rich datasets acquired by the imaging system, as well as visualization techniques for efficient analysis of the derived data products. In this way, the present systems and methods can help specialty crop growers reduce costs, save resources, and optimize crop yield.

Abstract: A respective confidence level of a potential collision is determined for each of a plurality of targets based on each target's heading angle and distance from a host vehicle. A threat number is determined for each target when its respective confidence level is above a threshold. A vehicle component is actuated based on the threat number.

Abstract: A vehicle guidance system, including: surface-mounted pressure sensors mounted on a vehicle; an air data estimation controller including: a preprocessor that sets initial values for angle of attack and sideslip angle, determines a converged value for the angle of attack using the initial values and values of one or more first sets of three sensors, each first set of sensors are located among three different planes that are parallel to the ground, and provides a converged sideslip angle value based on the converged value and values of one or more second sets of three sensors, each second set of sensors located among three different planes that are perpendicular to the ground; a processor that estimates air data based on the converged value for the angle of attack and the converged sideslip angle value; and processor that provides an output for adjusting orientation of a vehicle based on the air data.

Abstract: Systems and methods for determining a flight path of an aircraft are provided. In one embodiment, a method can include identifying one or more parameter(s) associated with a moving target. The method can include determining a moving circular flight path associated with the moving target based at least in part on the parameter(s) associated with the moving target. The method can include identifying one or more condition(s) associated with at least one of the aircraft and the moving circular flight path. The method can include determining a flight path of the aircraft from a location of the aircraft to the moving circular flight path based at least in part on the parameter(s) associated with the moving target and the condition(s) associated with at least one of the aircraft and the moving circular flight path.

Abstract: An agricultural monitoring system, the agricultural monitoring system comprising: an imaging sensor, configured and operable to acquire image data at submillimetric image resolution of parts of an agricultural area in which crops grow, when the imaging sensor is airborne; a communication module, configured and operable to transmit to an external system image data content which is based on the image data acquired by the airborne imaging sensor; and a connector operable to connect the imaging sensor and the communication module to an airborne platform.

Abstract: Techniques for using an aerial vehicle to provide a data service are provided. For example, information about a request for the data service is accessed. The request is sent to a provider computing device and identifies a user computing device to receive the data service. The provider computing device is configured to provide the data service. A location associated with providing the data service is determined based on the request. The aerial vehicle is flown to the location. The aerial vehicle includes a computing system configured to provide a portion of the data service. Based on detecting that the aerial vehicle is within a range of the location, the aerial vehicle provides the portion of the data service to the user computing device by using, for example, the computing system.

Abstract: In a vehicle travel control apparatus configured to determine a target acceleration of an own vehicle based on an inter-vehicle distance to a predicted cutting-in vehicle predicted to cut in between the own vehicle and a following target vehicle as well as an inter-vehicle distance to the following target vehicle, it is necessary to notify a driver of the presence of the predicted cutting-in vehicle at an appropriate timing. A cutting-in probability, which is a probability that the predicted cutting-in vehicle carries out the cutting in, is acquired, and information on the predicted cutting-in vehicle is notified to the driver from a time point when a state where the cutting-in probability is higher than a start probability threshold has continued for a predetermined period to a time point when a state where the cutting-in probability is lower than an end probability threshold has continued for a predetermined period.

Abstract: In an example, a method includes determining, at a host device, a power state of a digital input/output device, and transmitting a clock signal having a first frequency from the host device to the input/output device responsive to a determination that the input/output device is in a lower power state. The method also includes determining, at the host device, that the input/output device has transitioned into a higher power state, and transmitting a clock signal having a second frequency from the host device to the input/output device responsive to a determination that the input/output device has transitioned into the higher power state. The first frequency is lower than the second frequency.

Abstract: There is provided a system including a non-transitory memory storing an executable code and a hardware processor executing the executable code to receive a plurality of training contents depicting a plurality of activities, extract training object data from the plurality of training contents including a first training object data corresponding to a first activity, extract training scene data from the plurality of training contents including a first training scene data corresponding to the first activity, determine that a probability of the first activity is maximized when the first training object data and the first training scene data both exist in a sample media content.

Abstract: A method and apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction includes providing, using a camera fixed to a radar, an image representing a target area, receiving an indication of a position in the image, the indicated position corresponding to a position in the target area, determining, using a radar, the actual direction of the projectile, determining a launch position of the projectile, determining, from the launch position and the corresponding position, the predetermined direction and determining the deviation between the actual direction of the projectile and the predetermined direction. The indicating step include rotating the camera and radar to have the position in the target area presented at a center or with a predetermined offset form the center in the image.

Abstract: This disclosure describes systems, methods, and apparatus for automating the verification of aerial vehicle sensors as part of a pre-flight, flight departure, in-transit flight, and/or delivery destination calibration verification process. At different stages, aerial vehicle sensors may obtain sensor measurements about objects within an environment, the obtained measurements may be processed to determine information about the object, as presented in the measurements, and the processed information may be compared with the actual information about the object to determine a variation or difference between the information. If the variation is within a tolerance range, the sensor may be auto adjusted and operation of the aerial vehicle may continue. If the variation exceeds a correction range, flight of the aerial vehicle may be aborted and the aerial vehicle routed for a full sensor calibration.

Abstract: Techniques disclose an incrementally expanding object detection model. An object detection tool identifies, based on an object detection model, one or more objects in a sequence of video frames. The object detection model provides an object space including a plurality of object classes. Each object class includes one or more prototypes. Each object is classified as being an instance of one of the object classes. Each identified object is tracked across at least one of the frames. The object detection tool generates a measure of confidence for that object based on the tracking. Upon determining that the measure of confidence exceeds a threshold, the object detection tool adds a prototype of the instance to the object detection model.

Abstract: A method for optimizing the position and size of a search window in a tracking system is disclosed. According to some embodiments of the present invention, the method may comprise: calculating a velocity of a tracked object based on comparison of at least two previously captured consecutive frames; calculating an expected position of the tracked object in a subsequent frame based on calculated velocity of the tracked object; determine possible positions of the tracked object in the subsequent frame, based on the last known position of the tracked object, status of the tracked object, the expected position and the acceleration of the tracked object; and optimizing the size and position of the search window within the subsequent frame so that the search window covers the expected position and at least one of the possible positions of said tracked object.

Abstract: An information processing apparatus is provided, in which content and position information generated independently of each other are recorded in a recording medium. The apparatus includes a recording medium in which the content and the position information are recorded and a deletion unit deleting position information temporally associated with a piece of the content from the recording medium when the piece of content is deleted from the recording medium.

Abstract: Methods and apparatus track an object with a first camera causing a second camera to also track the object. The object is a moving object. Geospatial coordinates, including an elevation or altitude of a camera are determined on the camera. A pose of the camera, including a pitch angle and an azimuth angle are also determined. Azimuth is determined by a digital compass. A camera pose including pitch is determined by accelerometers and/or gyroscopes. Cameras are communicatively connected allowing to display an image recorded by one camera being displayed on a second camera. At least one camera is on a movable platform with actuators. Actuators are controlled to minimize a difference between a first image of the object and a second image of the object. Cameras are part of a wearable headframe.

Abstract: A multi-function radio frequency (MFRF) module integrates command guidance, active and semi-active terminal guidance (and possibly passive) and fuzing sensors for gun-launched munitions into a single assembly. The MFRF module can be incorporated into a variety of different gun-launched munitions to execute missions currently performed by guided missiles. The MFRF module is programmable during munition activation to select the guidance mode, active or semi-active, and a primary fuze mode, proximity or height of burst.

Abstract: A system and a method for increasing a rate of transfer of data between a radio frequency (RF) generator and a host computer system is described. The rate of transfer of data is increased by implementing dedicated physical layers associated with the RF generator and the host computer system and a dedicated physical communication medium between the RF generator and the host computer system. Moreover, a dual push operation is used between the RF generator and the host computer system. There is no request for data sent from the RF generator to the host computer system or from the host computer system to the RF generator.

Abstract: A method and system of synthesizing impedance in a radio frequency (RF) amplifier includes receiving a voltage signal at a passive mixer. The passive mixer down-converts the voltage signal into a baseband frequency. The method includes converting the voltage signal into a digital signal. Further, the method includes performing convolution of the digital signal with an impulse response. The impulse response is of a low Q impedance and is programmable. Furthermore the method includes generating a current signal based on output of the convolution. Furthermore the method includes performing up-conversion of the current signal in the passive mixer. The passive mixer performs impedance transformation of the low Q impedance. Moreover, the method includes providing the current signal via the passive mixer to synthesize desired impedance in the RF amplifier, thereby controlling frequency response of the RF amplifier.

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

Abstract: According to one aspect, a flight controller constructed to control a parafoil in flight from a starting location to a target location is provided. The flight controller includes an interface constructed to connect to one or more actuators and one or more wind sensors, a memory, a processor coupled to the memory, the interface, and a flight manager component executable by the processor. The flight manager component is configured to identify the target location and the starting location, receive wind data, determine a relationship between a ground reference frame (GRF) and a wind fixed frame (WFF) based on the wind data, generate a trajectory between the starting location and the target location in the WFF, determine a desired heading based on the trajectory and the relationship between the GRF and the WFF, and generate an actuator control signal based on the desired heading to adjust a heading of the parafoil.

Abstract: A stabilization control method for a satellite tracking antenna disclosed herein includes outputting a monopulse signal and a gyro signal through a satellite tracking antenna having a gyro mounted thereto, under a situation that disturbance is applied to the satellite tracking antenna, inputting the output monopulse signal and gyro signal into a Kalman filter for stabilization of the satellite tracking antenna, defining a state vector of the Kalman filter based on a pointing-error angle for the satellite tracking, corresponding to the monopulse signal, and a pointing-error angular velocity for the satellite tracking, corresponding to the gyro signal, predicting an original monopulse signal corresponding to a state prior to distortion of the monopulse signal based on the defined state vector, and continuously updating the prediction of the original monopulse signal, and carrying out the stabilization control for the satellite tracking antenna by using the predicted original monopulse signal as a pointing-error

Abstract: A flight safety assembly onboard an aerial vehicle includes a first sensor configured to sense first information related to flight of the aerial vehicle and a second sensor configured to sense second information related to the flight of the aerial vehicle. A sensor input is adapted to receive third information related to the flight of the aerial vehicle. A processor is operably coupled to the first sensor, the second sensor, and the sensor input. The processor is configured to determine three independent instantaneous impact points for the aerial vehicle by independently analyzing each of the first information, the second information and the third information. The processor is also configured to generate three independent onboard flight termination indicators for each of the three independent instantaneous impact points that intersects with a region to be protected.