Abstract: Determining, broadcasting and using reference pressure data in a network of transmitters. Particular embodiments described herein include machines that select atmospheric data from weather stations within a transmitter network, use the selected atmospheric data to determine a reference atmospheric value, and transmit the reference atmospheric value from a transmitter to a mobile device for use in estimating an altitude of the mobile device. The atmospheric data may include any of reference pressures form the weather stations, measured temperatures from the weather stations, or reference temperatures from the weather stations. The reference atmospheric value may include a reference pressure value of a reference altitude, or a reference temperature value.

Abstract: Systems and methods for controlling a head-up display (HUD) in a vehicle are disclosed herein. One embodiment deactivates the HUD in response to a command from a driver of the vehicle; assigns a level of urgency to an item of information associated with a current vehicular context; and activates the HUD to display the item of information to the driver, when the level of urgency exceeds a predetermined threshold.

Abstract: A ground weather center may transmit information requests that carry at least one meteorological specific triggering command. An airborne system may translate the triggering command into detectable meteorological conditions and may arm the trigger(s) for specific weather sensors accordingly and downlink information upon the airborne system detects the triggering conditions. By using such a triggering command, the airborne system may be able transmit the same amount of valuable information with less bandwidth by reducing the number of redundant downlinked packets.

Abstract: A method, includes saving in-flight data from an aircraft during a simulated training exercise, wherein the in-flight data includes geospatial locations of the aircraft, positional attitudes of the aircraft, and head positions of a pilot operating the aircraft, saving simulation data relating to a simulated virtual object presented to the pilot as augmented reality content in-flight, wherein the virtual object was programmed to interact with the aircraft during the simulated training exercise and representing the in-flight data from the aircraft and the simulation data relating to the simulated virtual object as a replay of the simulated training exercise.

Abstract: An unmanned aerial vehicle (UAV) may include a communication interface and a pressure sensor configured to measure barometric pressure. The UAV may also include a processor configured to generate a request for elevation data and barometric pressure data and transmit, via the communication interface, the request to the at least one other device. The processor may also be configured to receive, from each of the at least one other device, elevation data and barometric pressure data, and estimate the elevation of the UAV based on the measured barometric pressure, the received elevation data and the received barometric pressure data.

Abstract: Methods, systems, and program products of inspecting solar panels using unmanned aerial vehicles (UAVs) are disclosed. A UAV can obtain a position of the Sun in a reference frame, a location of a solar panel in the reference frame, and an orientation of the solar panel in the reference frame. The UAV can determine a viewing position of the UAV in the reference frame based on at least one of the position of the Sun, the location of the solar panel, and the orientation of the solar panel. The UAV can maneuver to the viewing position and point a thermal sensor onboard the UAV at the solar panel. The UAV can capture, by the thermal sensor, a thermal image of at least a portion of the solar panel. A server onboard the UAV or connected to the UAV can detect panel failures based on the thermal image.

Abstract: Described herein are systems, methods, and apparatuses for performing a user-less payment for an item upon its delivery by an unmanned delivery vehicle. The unmanned delivery vehicle may navigate to a delivery location, receive payment information, initiate a payment transaction with a remote server, and release the item at a specified location upon successful completion of the payment transaction. Upon arrival of the unmanned delivery vehicle, a wireless data transmission device may send payment information to a remote server, and the remote server may provide the unmanned delivery vehicle with an indication of whether the item can be released and a specific location at which the item can be released.

Abstract: An aircraft includes first units each including a first sensor, a rotary wing, a driver, and a first drive controller. The first drive controller is configured to generate a drive signal of the rotary wing on the basis of a flying route of the aircraft and a control law based on a flying state detected by the first sensor, and output the drive signal to the driver configured to drive the rotary wing. The control laws of the respective first drive controllers are equal to each other between the first units. The first drive controllers are each configured to generate the drive signals that correspond to all of the first units. The drivers are each configured to drive the corresponding rotary wing on the basis of corresponding one of the drive signals that correspond to all of the first units and that are generated by the first drive controllers.

Abstract: Avionics systems, aircraft, and methods are provided. An avionics system for an aircraft includes a trajectory modeling system and a Terrain Awareness Warning System (TAWS). The trajectory modeling system is programmed to determine a current performance capability of the aircraft and to generate potential escape data based on the current performance capability of the aircraft. The TAWS is programmed to generate a terrain margin using a TAWS algorithm based on the potential escape data and to generate a warning based on the terrain margin.

Abstract: According to one embodiment, a sensor includes a base body, a first supporter fixed to the base body, and a first movable part separated from the base body. The first movable part includes a first movable base part supported by the first supporter, a second movable base part connected with the first movable base part, and a first movable beam. The first movable beam includes a first beam, a first movable conductive part, and a first connection region. The first beam includes a first beam portion, a second beam portion, and a third beam portion between the first beam portion and the second beam portion. The first beam portion is connected with the first movable base part. The second beam portion is connected with the second movable base part. The first connection region connects the third beam portion and the first movable conductive part.

Abstract: Methods and associated systems for autonomous package delivery utilize a UAS/UAV, an infrared positioning senor, and a docking station integrated with a package delivery vehicle. The UAS/UAV accepts a package for delivery from the docking station on the delivery vehicle and uploads the delivery destination. The UAS/UAV autonomously launches from its docked position on the delivery vehicle. The UAS/UAV autonomously flies to the delivery destination by means of GPS navigation. The UAS/UAV is guided in final delivery by means of a human supervised live video feed from the UAS/UAV. The UAS/UAV is assisted in the descent and delivery of the parcel by precision sensors and if necessary by means of remote human control. The UAS/UAV autonomously returns to the delivery vehicle by means of GPS navigation and precision sensors. The UAS/UAV autonomously docks with the delivery vehicle for recharging and preparation for the next delivery sequence.

Abstract: A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.

Abstract: An aerial vehicle and a method of taking a measurement using a sensor mounted on an aerial vehicle. The aerial vehicle has one or more propellers and one car more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly. A sensor is mounted on the aerial vehicle. The method includes operating the one or more motors to drive the one or more propellers to cause the vehicle to fly. At a first time instant, the one or more motors are slowed down or turned off. When the one or more motors are slowed down or turned off, a measurement is taken using the sensor; at a second time instant, which is after the measurement has been taken using sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly.

Abstract: Disclosed is a method of operating an electronic apparatus, the method including identifying first position information on a map based on address information input by a user requesting a delivery service, identifying second position information corrected from the first position information on the map, updating information by matching the address information and the second position information on the map, and providing the updated information.

Abstract: A method of automatically determining a flight trajectory of a vertical take-off and landing aircraft having vectorable propulsion can be used to improve flight efficiency. The method includes receiving one or more aircraft flight constraints, inputting the aircraft flight constraints to a trajectory planning algorithm to determine a minimum energy aircraft transition trajectory, and outputting a control schedule to fly the aircraft to along the flight trajectory.

Abstract: A haptic feedback system to stimulate physical sensation of handling a fluid in virtual spaces. The system includes a physical vessel containing a solid object and mechanical means to move the solid object therein, a virtual reality module to track a position of the physical vessel and a corresponding virtual vessel, logic to simulate a fluid contained in the virtual vessel based on the tracked position of the virtual vessel, logic to calculate coordinates of a center of gravity for the simulated fluid based on the tracked position of the virtual vessel, logic to translate the calculated coordinates of the center of gravity for the simulated fluid into cylindrical coordinates to which to move the solid object in the physical vessel, and logic to send instructions to the mechanical means to move the solid object in the physical vessel based on the cylindrical coordinates to shift the weight of the physical vessel in accordance with the center of gravity of the simulated fluid in the virtual vessel.

Abstract: In one embodiment, a device in a serial network de-multiplexes a stream of traffic in the serial network into a plurality of data streams. The device determines that data from a particular data stream should be reported to an entity external to the serial network based on an event indicated by the data from the particular data stream. The device quantizes the data from the particular data stream. The device applies compression to the quantized data to form a compressed representation of the particular data stream. The applied compression is selected based on a data type associated with the data. The device sends a compressed representation of the particular data stream to the external entity as Internet Protocol (IP) traffic.

Abstract: There is provided a method of automatically landing a drone on a landing pad having thereon guiding-elements arranged in a pattern relative to a central region of the landing pad, comprising: receiving first image(s) captured by a camera of the drone, processing the first image(s) to compute a segmentation mask according to an estimate of a location of the landing pad, receiving second image(s) captured by the camera, processing the second image(s) according to the segmentation mask to compute a segmented region and extracting from the segmented region guiding-element(s), determining a vector for each of the extracted guiding-element(s), and aggregating the vectors to compute an estimated location of the central region of the landing pad, and navigating and landing the drone on the landing pad according to the estimated location of the central region of the landing pad.

Abstract: A motion planning method and system for aircraft, in particular for separately electrically driven, load-carrying and/or people-carrying multicopters, includes: a motion preliminary planning unit that executes a preliminary planning algorithm using a computer on the ground or on board an aircraft in question, by which algorithm a reference trajectory, emergency trajectories are determined at intervals along the reference trajectory and confidence intervals are determined along the reference trajectory, which confidence intervals specify a spatial volume in which to maneuver without a pre-planned path but that the aircraft can't leave or is able to leave only at predefined locations; a data store in which parameters of the reference trajectory, parameters of the confidence intervals and parameters regarding a permissible deviation of the aircraft from the reference trajectory are stored on the aircraft according to instructions of the motion preliminary planning unit; a real-time control unit on the aircraft f

Abstract: Automatic flight information determination device for automatically determining flight control information for an accompanying mobile machine accompanying a leader mobile machine, said device being adapted for collecting the location data of the leader mobile machine from among the actual location data derived from measurements relating to the current location of the leader mobile machine and the current trajectory data of the accompanying mobile machine, and of determining, on the basis of said location data collected, the information items for piloting the accompanying mobile machine as a function of a set of at least two values to be adhered to with respect to the location defined by the data collected, said values to be adhered to being representative of the values included among: a minimum vertical/flight level separation value, a minimum longitudinal/along track separation value, and a minimum lateral/between tracks separation value.

Abstract: A stability and command augmentation system for controlling an aircraft, comprising: a first member moveable by a pilot input device to a first position defining a first input; a second member moveable to a second position associated with a second input; and an adder device configured to add the first and second inputs and supply an output signal defining a command for an element to be controlled of the aircraft; the stability and command augmentation system comprises: a casing, a first and a second piston integrally movable with one another inside the casing and operatively connected to the second member; and control means configured to exert a first force on the first piston and a second force on the second piston; the second force is independent of the first force.

Abstract: Unmanned aircraft systems (UASs) and related techniques are provided to improve the operation of unmanned mobile sensor or survey platforms. A flight altitude estimation system includes a logic device configured to communicate with a communication module and a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the communication module is configured to establish a communication link with a base station associated with the mobile platform, and the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area. The logic device is configured to receive demark pressure data from a demark barometer coupled to the base station and determine a differential flight altitude estimation based, at least in part, on received flight pressure data and demark pressure data, a reference flight pressure and a reference demark pressure corresponding to a flight initiation location of the base station.

Abstract: Systems and methods are disclosed for traffic management for unmanned aerial vehicles (UAVs). The systems and methods define a network of waypoint computing devices having traffic corridors connecting the waypoint computing devices. Systems and methods receive suspend calls and initiate calls from waypoint computing devices and dynamically update the network so as to include additional waypoint computing devices and traffic corridor connections based on the initiate calls and to remove from the network waypoint computing devices and associated traffic corridors based on the suspend calls. The systems and methods determine a flight plan for the UAV in response to a request based on the updated network. The flight plan includes a plurality of traffic corridors connecting source and destination global coordinates included in the request. The systems and methods provide a response to the UAV including the flight plan.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Abstract: A distance sensor and a measured object are positioned at a known distance from each other. A measured distance between the distance sensor and the measured object is obtained from the distance sensor, where the distance sensor uses a plurality of signals at a plurality of angles to generate the measured distance. The known distance and the measured distance are compared in order to test the distance sensor and produce a test result.

Abstract: A flap slat control lever and a method for operating the lever are disclosed. The lever includes: a first displacement sensor to detect a displacement of the flap slat control lever and generate a first displacement detection signal; a second displacement sensor to detect the displacement of the flap slat control lever and generate a second displacement detection signal; a first control command module to receive the first displacement detection signal; and a second control command module to receive the second displacement detection signal, wherein the first control command module is in a standby state and the second control command module is in a working state.

Abstract: Systems, methods, and apparatus for sensor fault detection and identification using residual failure pattern recognition are disclosed. In one or more embodiments, a method for sensor fault detection and identification for a vehicle comprises sensing, with sensors located on the vehicle, data. The method further comprises performing majority voting on the data for each of the types of data to generate a single voted value for each of the types of data. Also, the method comprises generating, for each of the types of data, estimated values by using some of the voted values. In addition, the method comprises generating residuals by comparing the estimated values to the voted values. Further, the method comprises analyzing a pattern of the residuals to determine which of the types of the data is erroneous to detect and identify a fault experienced by at least one of the sensors on the vehicle.

Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.

Abstract: Vertical take-off/landing and horizontal straight flight aircraft for transportation of passengers, cargo, and/or goods are described herein. The aircraft have increased thrust and flight speed; improved controllability and maneuverability of flight; increased safety of take-off, landing and touchdown of the aircraft; reduction in the weight and size characteristics of aircraft. An aircraft includes redistributed, assembled and interconnected small-sized independently operating electric motors of the main rotors obtained by defragmentation of the propeller-motor group (PMG), spaced from each other and forming a small-sized independently operating PMG located at certain distance from the longitudinal axis of the aircraft, and each small-sized main rotor in each small-sized independently operating PMG is connected to the small-sized independently operating electric motor. The small-sized independently operating PMGs are installed inside the screens, on the beams of the common frame and/or on tubes.

Abstract: An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.

Abstract: An aerial vehicle including a first wing structure and a second wing structure which intersects the first wing structure perpendicularly at a position offset from a midpoint of a transverse axis of the first wing structure in a direction towards a first wingtip of the first wing structure. The aerial vehicle may further include a first set of at least two propellers with respective propeller rotational axes disposed side-by-side along a portion of the first wing structure extending between the midpoint of the transverse axis of the first wing structure and a second wingtip of the first wing structure. The aerial vehicle may further include a second set of at least two propellers with respective propeller rotational axes disposed side-by-side along a first portion of the second wing structure extending from a first surface of the first wing structure.

Abstract: Example embodiments may relate to web interfaces for a balloon-network. For example, a computing device may display a graphical interface that provides information related to a balloon network configured to provide service in a geographic area, where the graphical interface includes a map. The computing device may receive real-time bandwidth data related to balloons in the balloon network, where the balloons are each configured to change position via altitudinal movement and via horizontal movement with respect to the ground. Based at least in part on the received real-time bandwidth data, the computing device may display, on the map, a visual representation of bandwidth information corresponding to one or more regions in the geographic area, where the visual representation of bandwidth information updates from time to time based at least in part on a change in position of one or more balloons in the balloon network.

Abstract: In measurement using infrared images that are obtained by nighttime aerial photography, a correspondence relationship between the infrared images is determined with high accuracy by the following method. In this method, agricultural land is photographed from the air at night by using an infrared camera mounted on a UAV. In the state in which multiple infrared light emitting points are installed on agricultural land, the agricultural land is photographed multiple times by the infrared camera while the UAV flies at night in such a manner that a part of the agricultural land is commonly contained in multiple infrared photographic images. Then, a correspondence relationship between the multiple infrared photographic images is determined by using bright points of the infrared light emitting points in the part of the agricultural land commonly contained in the infrared photographic images.

Abstract: A method of controlling a movable object to track a target includes determining a difference between a desired height and a measured height of the movable object, determining a reference speed of the movable object or the target, and adjusting the movable object based on the reference speed and the difference between the desired height and the measured height.

Abstract: Provided are a flying object control device, a flying object, and a program that can suppress occurrence of unintended turning in the flying object. A flying object control device has: a command value generation unit that generates a turning torque command value on the basis of a turning torque target value which is a target value of turning torque of a flying object; and an external disturbance countermeasure value generation unit that generates an external disturbance countermeasure value in accordance with turning torque generated by external disturbance, on the basis of the turning torque command value generated by the command value generation unit and a sensor detection value acquired by using a sensor provided to the flying object, wherein the command value generation unit generates the turning torque command value by subtracting the external disturbance countermeasure value generated by the external disturbance countermeasure value generation unit from the turning torque target value.

Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.

Abstract: An automatic takeoff flight control system controls an aircraft to automatically follow a predetermined set of control parameters upon taking off from the ground using both longitudinal and lateral control laws. The control system provides takeoff speed reduction to thereby reduce the takeoff distance (TOD) and, as a consequence, increase the takeoff weight (TOW). The control system sets the horizontal stabilizer (HSTAB) in a non-trimmed condition—named “mistrim”; and provides beta for optimum climb at takeoff, through lateral-directional surfaces commands.

Abstract: A control method includes obtaining one or more attitude parameters of a gimbal of an unmanned aerial vehicle (UAV) and adjusting one or more attitude parameters of the UAV according to the one or more attitude parameters of the gimbal.

Abstract: There is provided a flight control system including a virtual path setting unit, a first evaluation unit, a path determination unit, and a flight controller. The virtual path setting unit is configured to set a plurality of virtual paths other than a current path of an aircraft at a prescribed timing. The first evaluation unit is configured to evaluate envelope protection of each of the current path and the plurality of virtual paths. The path determination unit is configured to determine a path among the current path and the plurality of virtual paths, based on an evaluation result of the envelope protection. The flight controller is configured to control flight of the aircraft based on the determined path.

Abstract: In an example, a method of generating flight paths for navigating an aircraft is provided. The method includes hovering the aircraft at a predetermined hover point. The predetermined hover point corresponds to a first takeoff waypoint of a first trajectory of the aircraft. The method includes scanning at least a portion of a first flight path of the first trajectory. The method includes determining that an obstacle obstructs the first flight path of the first trajectory. The first flight path begins at the first takeoff waypoint. The method includes determining a second takeoff waypoint. Determining the second takeoff waypoint includes assigning the first flight path to begin at the second takeoff waypoint. The method includes changing the first flight path of the first trajectory in accordance with the second takeoff waypoint, thereby forming a second flight path of a second trajectory.

Abstract: A control system (200) using fixed point computation avoids overflow conditions by limiting the internal quantities ensuring that contributing calculations from various parts of the control loop never add up to an overflow. Various parts of a control loop e.g. proportional terms can be prioritised over other parts, e.g. integral and differential terms and ensuring that the overall total resulting when the separate terms are summed together never exceeds the maximum or minimum imposed limits. Variable limit calculator circuits (211,219) revise the limits according to the output of the higher priority control path(s). The revised limits cascade down through each contributor, eventually allowing the lowest priority control path the smallest authority. The control system may be applied to control of a drive motor (111) for an aircraft inceptor (103).

Abstract: The position of a UAV within a three-dimensional space is changed based on a change in position of a controller of the UAV. First and second sensor data are produced using sensors of the controller to maintain stable altitude output for the UAV. The first sensor data indicates a geolocation of the controller, and the second sensor data indicates a barometric pressure of an environment in which the controller is located. The first and second sensor data are post-processed using a complementary filter based on respective altitude measurements of the first and second sensor data to determine an altitude of the controller. A position of the controller is determined within a three-dimensional space based on the altitude. Data indicative of the position of the controller within the three-dimensional space is then transmitted to the UAV to cause a change in a position of the UAV within the three-dimensional space.

Abstract: An aircraft control system for an unmanned aircraft comprising a forward propulsion system comprising a forward thrust engine and a vertical propulsion system comprising a vertical thrust engine. The aircraft control system may include a controller comprising an input coupled to receive a velocity signal indicating a determined amount of forward velocity and being configured to generate a pitch angle command associated with the determined amount of forward velocity; a splitting block comprising an input to receive the pitch angle command and being configured to generate a second pitch angle command and a forward thrust engine throttle command based on a bounded pitch angle for the unmanned aircraft; and an output coupled to provide the second pitch angle command to the vertical propulsion system and the forward thrust engine throttle command to the forward propulsion system.

Abstract: An aerial vehicle includes an airframe; vertical propulsion units, and a controller. The vertical propulsion units are mounted to the airframe and include propellers oriented to provide vertical propulsion to the aerial vehicle. The vertical propulsion units are physically organized in quadrants on the airframe with each of the quadrants including two or more of the vertical propulsion units. The controller is coupled to the vertical propulsion units to control operation of the vertical propulsion units. At least two of the vertical propulsion units in each of the quadrants are adapted to counter-rotate from each other during flight of the aerial vehicle.

Abstract: The present invention discloses improvements to mechanical and electro-mechanical force simulators for aircraft pilot controllers, and particularly foot-actuated controllers. In particular, the invention replaces conventional foot-actuated, pilot controller systems—namely, those that employ multiple, discrete, motion control subsystems to control the various force simulation and trim functions used in modern aircraft to assist pilot control of a given axis of flight—with a single motion control system. The invention accomplishes this in part by eliminating the force-feel spring used in conventional, federated, foot-actuated, motor-coupled pilot controllers.

Abstract: An unmanned aerial vehicle (UAV) includes a power device communicatively configured to provide power for the UAV and one or more processors coupled to the power device. The one or more processors are configured to obtain a flight velocity of the UAV corresponding to the power, obtain an image frame as a keyframe in response to that the flight velocity satisfies a preset condition, and control the UAV to hover using the keyframe as a reference object.

Abstract: A trailer assist system for a vehicle includes a plurality of sensors disposed at a vehicle, a trailer sensor disposed at a rear portion of a trailer and having a field of sensing at least rearward of the trailer, and a control having a processor operable to process data captured by the sensors. A display screen displays an area rearward of the trailer. Responsive to a user input selecting a target area present in the displayed image, the control, via processing of data captured by the sensors, is operable to determine a path of travel for the vehicle and trailer to follow to maneuver the vehicle and trailer toward a target location represented by the selected displayed target area. The control, responsive to determination of the path of travel, controls at least steering of the vehicle to maneuver the vehicle and trailer along the determined path of travel.

Abstract: A control system having a variable operator interface (VOI) is disclosed, and includes one or more processors and a memory coupled to the processors. The memory stores program code causing the control system to detect an existence and first direction of an operator control input to one or more active inceptors being backdriven from an operator on inceptor detector (OID). The control system is caused to compare the first direction of the operator control input with a second direction of one or more zero-force detent rates to determine a variance and interprets the operator control input as inadvertent based on the variance. In response to interpreting the operator control input as inadvertent, the control system is caused to limit the operator control input to reduce or substantially eliminate movement of the machine caused by inadvertent input by modifying the operator control input based on one or more command modifiers.

Abstract: A satellite attitude data fusion system and method is disclosed, applicable to the earth satellite environment to estimate attitude data of the satellite. When the satellite attitude data fusion system of the present invention is used to perform the satellite attitude data fusion method, the first step is to perform a body rates quaternion attitude data processing operation. Then, the next step is to perform an attitude/rates data fusion processing operation, wherein an attitude data fusion algorithm module receives the first IAE result data from the first EKF, and the second JAE result data from the second EKF, and performs an attitude/rates data fusion algorithm in a subsystem level to evaluate an attitude estimation JAE performance.

Abstract: An aircraft is provided including at least one pilot input and a flight control system n communication with the at least one pilot input. The flight control system is operable in a manual mode and a pointing mode. In the manual mode, a velocity, position, and attitude of the aircraft are controlled manually, and in the pointing mode, at least one of the velocity and position of the aircraft is controlled by the flight control system and at least one of the attitude and heading of the aircraft is controlled manually.