Abstract: Telematics systems and methods are described for generating interactive animated guided user interfaces (GUIs). A telematics cloud platform is configured to receive vehicular telematics data from a telematics device onboard a vehicle. A GUI value compression component determines, based on the vehicular telematics data, a plurality of GUI position values and a plurality of corresponding GUI time values. A geospatial animation app receives the plurality of GUI position values and the plurality of corresponding GUI time values. The geospatial animation app implements an interactive animated GUI that renders a plurality of geospatial graphics or graphical routes on a geographic area map via a display device. The geospatial graphics or graphical routes are rendered to have different visual forms based on differences between respective GUI position values and corresponding GUI time values.

Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.

Abstract: A real-time calibration system and method for a mobile device having an onboard magnetometer uses an estimator to estimate magnetometer calibration parameters and a magnetic field external to the mobile device (e.g., the earth magnetic field). The calibration parameters can be used to calibrate uncalibrated magnetometer readings output from the onboard magnetometer. The external magnetic field can be modeled as a weighted combination of a past estimate of the external magnetic field and the asymptotic mean of that magnetic field, perturbed by a random noise (e.g., Gaussian random noise). The weight can be adjusted based on a measure of the statistical uncertainty of the estimated calibration parameters and the estimated external magnetic field. The asymptotic mean of the external magnetic field can be modeled as a time average of the estimated external magnetic field.

Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.

Abstract: This method controls the drone in order to flip through a complete turn about its roll axis or its pitching axis. It comprises the steps of: a) controlling its motors simultaneously so as to impart a prior upward vertical thrust impulse to the drone; b) applying different and non-servo-controlled commands to the motors so as to produce rotation of the drone about the axis of rotation of the flip, from an initial angular position to a predetermined intermediate angular position; and then c) applying individual control to the motors, servo-controlled to a reference target trajectory, so as to finish off the rotation of the drone through one complete turn about the axis of rotation, progressively from the intermediate angular position with a non-zero angular velocity to a final angular position with a zero angular velocity.

Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.

Abstract: A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.

Abstract: The disclosure describes, in one aspect, a control system for controlling a braking system. The control system includes a parking brake operatively to at least one wheel, a park brake override mechanism operatively associated with the parking brake, an inching pedal operatively coupled to a transmission, a shift lever operatively coupled to the transmission, at least one sensor operatively coupled to the parking brake to detect when the parking brake is engaged, at least one sensor operatively coupled to the inching pedal to detect a depression of the inching pedal, and at least one sensor operatively coupled to the shift lever for detecting at least one of a forward or reverse gear selection. The control system further includes a controller operatively coupled to the at least one sensors to receive corresponding signals and adapted to control the engagement of the parking brake when the inching pedal is depressed and the at least one of the forward or reverse gear selections is desired.

Abstract: The invention relates to methods and systems for controlling the speed of an aircraft. The methods and systems disclosed herein are particularly advantageous for unmanned aerial vehicles. A system may include an outer-loop controller, wherein the outer-loop controller is arranged to receive one or more target flight variables and to output a nominal target pitch; an inner-loop controller arranged to receive a target pitch and output a control signal for controlling at least one aircraft control device; and a saturation module arranged to receive a nominal target pitch and to output a target pitch for the inner-loop controller, wherein the nominal target pitch is limited between an upper bound and a lower bound by the saturation module to generate the target pitch.

Abstract: A six degree-of-freedom trajectory linearization controller (TLC) architecture (30) for a fixed-wing aircraft (46) is set forth. The TLC architecture (30) calculates nominal force and moment commands by dynamic inversion of the nonlinear equations of motion. A linear time-varying (LTV) tracking error regulator provides exponential stability of the tracking error dynamics and robustness to model uncertainty and error. The basic control loop includes a closed-loop, LTV stabilizing controller (12), a pseudo-inverse plant model (14), and a nonlinear plant model(16). Four of the basic control loops (34, 36, 40, 42) are nested to form the TLC architecture (30).

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.

Abstract: A flight control system of an aircraft and a flight control method of the aircraft are provided in which the overrunning an operation limitation on a flight condition can be prevented even when a pilot operates a flight control device fast.

Abstract: Upon receiving first data, a stop control unit (211) performs control such that a transportation vehicle (200) stops at a first stop position at which the transportation vehicle (200) can load the article onto a second apparatus. Upon receiving second data, the stop control unit (211) performs control such that the transportation vehicle (200) stops at a second stop position corresponding to a first apparatus.

Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.

Abstract: A method and a device for activating an automatic piloting mode of an aircraft are disclosed. The device can include means for engaging an automatic pilot mode, when (i) the current distance of the aircraft with respect to a reference position on the ground belongs to a determined distance range, and (ii) the current height of the aircraft is at most equal to a reference height associated to the automatic pilot mode.

Abstract: A flight control system is configured for controlling the flight of an aircraft utilizing a three control loop design to robustly increase system performance. An inner loop comprises an improved linear quadratic regulator (LQR) search method, and an outer loop comprises a classic feedback summary gain design. A third loop comprises a steady state trim search method.

Abstract: An airport management system having a memory storing surface management data for aircraft at an airport and a processor calculating a metric using the surface management data and generating a recommendation for the aircraft based on the calculated metric. A computer readable storage medium including a set of instructions executable by a processor, the set of instructions operable to receive surface management data for aircraft at an airport, calculate a metric using the surface management data and generate a recommendation for the aircraft based on the calculated metric.

Abstract: A flight control system and method for controlling the flight of a fixed-wing model aircraft is disclosed. The flight control system may actively sense the condition when the wings of the model aircraft are not level to the horizon. The flight control system may then command the servo(s) to control movement about the roll and the yaw axes of the aircraft in order to level the wings to the horizon. In addition, the flight control system may limit the maximum bank angle that can be achieved even when full roll control is commanded by the operator. The flight control system in accordance with the present disclosure may allow inexperienced operators to fly model aircraft successfully by eliminating/mitigating adverse effects that may cause the operators to lose control.

Abstract: A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system. According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations.

Abstract: An inverter for an electric vehicle includes a speed instruction generating unit, a frequency voltage converting unit, an integrator and a 2-to-3 phase converter. The speed instruction generating unit outputs a speed instruction for changing the rotational frequency of an electric motor based on the on/off of a signal outputted from the accelerator pedal. The frequency voltage converting unit outputs a voltage instruction based on the frequency of the speed instruction. The integrator outputs a rotational angle by performing integration on the frequency of the speed instruction. The 2-to-3 phase converter receives the voltage instruction and the rotational angle and converts the received voltage instruction and rotational angle into three-phase voltage instructions.

Abstract: The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t1), and two arcs of the same radius linking respectively the ends of each branch, the two arcs being traversed in a second time (t2), the holding circuit comprising an exit point situated at the end of one of the branches is characterized in that the distance of the branches of the holding circuit for the last two loops performed are adjusted so that the aircraft is substantially in proximity to the exit point when the duration (D) has elapsed.

Abstract: A method of determining the appropriateness of satellite orbit modeling is provided. The method includes calculating values of parameters, that the predetermined model has, on the basis of predicted position data including a first predicted position at a first point of time and a second predicted position at a second point of time of a positioning satellite in time series, calculating a first and a second calculated positions of the positioning satellite derived from the predetermined model by using the values of the parameters; and determining the appropriateness of the predetermined model using the values of the parameters, on the basis of first difference between the first predicted position and the first calculated position, and seconded difference between the second predicted position and the second calculated position. The predetermined model is used when approximating a satellite orbit of the poisoning satellite.

Abstract: Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously.

Abstract: A preferred embodiment of a method for fine-tracking operator assistance for controlling movement of an object toward a target combines an operator input for guiding the object toward the target with a sensor-derived input from sensor measurement of the object's position relative to the target's position. The combined input is separated into low and high frequency content, and a Low Frequency Authority Limit component applies a pre-determined gain over a selected range to the low frequency content, while a High Frequency Authority Limit component applies a pre-determined gain over a selected range to the high frequency content. The low-frequency gain output is combined with the high-frequency gain output as a total control input for control of the object relative to the target.

Abstract: Systems and methods are disclosed herein to provide trim for a vehicle, such as an aircraft. For example, a method for providing trim may include generally simultaneously determining values for a plurality of trim variables in a plurality of degrees of freedom. In this manner, the iterative aspect of contemporary methods for providing trim is substantially mitigated and a more efficient, robust system is provided.

Abstract: A system for providing flight control instructions to an aircraft is claimed, wherein using aircraft position or velocity data, an outer control loop algorithm determines an aircraft target angle and an inner control loop algorithm outputs commands to cause the aircraft to achieve the target angle. Utilizing the commands outputted from the control loops, aircraft are able to autonomously take-off and land, station hold in a very precise manner, and fly in very close proximity to other objects with little chance of collision.

Abstract: A flight control system includes a collective position command module for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command module utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

Abstract: According to the invention, the method comprises checking (in 2) that the actual values of navigation parameters become closer to desired values within a predetermined time period. If this is not the case, the method comprises carrying out a predictive calculation (in 4) of the value of at least one particular parameter at consecutive future moments, and optionally transmitting an alarm (in 6) for the crew.

Abstract: A device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system includes a first unit for determining particular parameters concerning the aircraft, including the position of a power lever controlling the supply of fuel to the engine, and a second unit for determining, based on the particular parameters, whether the aircraft is in a state authorizing an action on the operating conditions of the engine and for issuing, as the case may be, a corresponding authorization signal.

Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.

Abstract: A control device includes a main servocontrol loop having a servocontrolled system, and a compensation device on the input side of the control device. The control device includes an internal loop that receives a first signal derived from the main servocontrol loop as input, and generates, as a function firstly of the first signal and secondly of a second signal characteristic of a parameter of the servocontrolled system, an error signal characteristic of the difference between said second signal and a theoretical signal determined using a model. The error signal being injected into the main servocontrol loop to correct the control of the servocontrolled system. The internal loop and/or the main loop include a variable gain amplifier, and the control device controls the gain of the variable gain amplifier.

Abstract: The present invention relates to a system and to an arrangement for evaluating in a defined space or area a delimited area (7) in which there is a degree of urgency greater than the degree of urgency in respect of the remainder of said space (1), wherein there is disposed within said space or area (1) a plurality of sensors which can evaluate the current or ongoing degree of urgency on the basis of one or more criteria. Selected sensors (2, 3, 4) shall be connected to computer equipment (50) which includes storage elements (52, 53, 54) adapted for storing current criteria-related values in a chosen time order, and wherein a calculating circuit (51) included in or connected to said computer equipment (50) is adapted for evaluation of a calculated degree of urgency on the basis of time-dependent changes in the evaluated current values, and determining and establishing the local orientation or geographic location of the delimited area through the medium of the calculating circuit.

Abstract: This method meets the constraints dictated by the instructed values of turning radius and by the instructed values of direction of approach in terms of route or course to be maintained at the obligatory points of passage. It includes, at the obligatory starting and arrival points of passage, in determining the turning paths that meet the instructed turning radius at these points. These turning paths are located, at each of the obligatory points of passage, on a pair of circles that are tangential to the points of passage, according to the instructed direction of approach valid at this point and oriented in this direction. Once these turning paths have been determined, a selection is made, from among them, according to simple rules, of an initial homing turning path and a final capture path that can be connected by a rectilinear linking path to go from the obligatory starting point of passage to the obligatory arrival point of passage while seeking the shortest possible distance of travel.

Abstract: A method and apparatus for use with an aircraft autopilot to prevent an aircraft part from striking the ground during near ground maneuvers by employing a protection circuit between the outer loop and the inner loop of the control chain between the autopilot and the control surface, the prevention circuit producing an output signal when there is a possibility of ground strike which output signal operates to reduce the control surface command signal from the inner loop to the control surface and thus be rapidly responsive to aircraft attitude changes that could produce ground strike.