Abstract: A method, apparatus, and computer program product for identifying a number of air states for a vehicle. A deflection of a control surface associated with an actuator is identified to form an identified deflection. A current in the actuator is identified to form a measured current. The number of air states for the vehicle is estimated using the identified deflection and the measured current.

Abstract: A method and device for reducing on an aircraft lateral effects of a turbulence. The device (1) includes means (2, 3, 5, 7, A1, A2) for calculating and applying a roll control command and a yaw control command enabling the side effects generated by a turbulence event to be attenuated on the aircraft.

Abstract: The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.

Abstract: A system and method of conveying missed approach procedures to a pilot are provided. The system and method include rendering a graphic representation of at least one leg of the missed approach procedure on a display. A determination is made as to whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure. At least one visual characteristic of the rendered graphic is selectively varied based on the determination of whether the aircraft is at least substantially flying the at least one leg of the missed approach procedure.

Abstract: A method and apparatus for a monitoring module. The monitoring module is configured to identify a difference between measured position information for a controller and expected position information for the controller. The monitoring module is configured to compare the difference with thresholds for managing an autopilot in a control system of a vehicle to form a comparison. The monitoring module is configured to manage an operation of the autopilot based on the comparison such that the autopilot remains operating when a backdrive system is inoperative and an intentional override of the autopilot is absent.

Abstract: There is herein described an unmanned aerial vehicle capable of inspecting, identifying, and/or categorising defects on objects to be inspected using visible and/or non-visible wavelengths from infra-red to ultraviolet. More particularly, there is herein described a remotely controlled or autonomous unmanned aerial vehicle capable of inspecting, identifying, and/or categorising defects on objects to be inspected using visible and/or non-visible wavelengths from infra-red to ultraviolet and displaying information relating to said defects.

Abstract: The invention relates to an unmanned air vehicle control system and method, designed such that, in one mission mode, the vehicle follows the mission route. The system comprises means (400, 450) for storing data indicating at least one auxiliary route (4000, 4001, 4002, 4003), such that each of a plurality of the mission route segments (10, 20), is assigned at least part (30, 31, 32, 33) of at least one auxiliary route. Furthermore, the system comprises route change means (53) designed for, as a response to a mission abandonment event (52), determining which part of which auxiliary route is assigned to the mission route segment where the vehicle is located, such that the vehicle can change the mission route to the corresponding auxiliary route.

Abstract: A drive control apparatus for an electric car as can correct a synchronizing frequency without employing beacons, is proposed. A wheel-diameter correction information output means includes wheel-diameter information calculation means for calculating wheel-diameter calculation information expressive of a wheel diameter of an electric car, on the basis of two-phase current information. The wheel-diameter correction information output means also includes selection output means. The selection output means selects a wheel-diameter data output WD1, the wheel-diameter calculation information WD2 based on the wheel-diameter calculation means, or wheel-diameter default information WD0, and it outputs wheel-diameter correction information WD. A synchronizing-frequency calculation means outputs synchronizing frequency information FM on the basis of axle rotational-frequency information FR and the wheel-diameter correction information WD.

Abstract: Disclosed is a method and device, which provide an enhanced ability to monitor the navigation of an aircraft during a phase of flight in which the aircraft is close to the ground in which the aircraft uses positional information supplied by a satellite positioning system for the navigation. A display screen is used to display a first characteristic sign representing a selected setpoint value for a height parameter of the aircraft. The display screen also displays a second characteristic sign representing a current auxiliary value expressed in the form of an achievable height parameter. An alert is emitted when the second characteristic sign is determined to be within a predetermined height value of the first characteristic sign, and the alert is shown in visual format on the display screen. An alarm is also emitted following a predetermined time after the alert is emitted, if the setpoint value is not replaced by a new setpoint value.

Abstract: In accordance with an embodiment, a system includes a plurality of subsystems cooperatively configured to control an aircraft in accordance with a plurality of manning modes, the system configured to perform fully automated control of the aircraft while operating in any of the plurality of manning modes, wherein the plurality of manning modes include: two onboard operators; one onboard operator; and no onboard operator, wherein the system receives input from a remotely located operator by way of wireless signals.

Abstract: Disclosed is a system and method for diverting from a flight plan without adjusting an autopilot by treating a heading change as the new leg of a flight plan. The present invention allows the pilot of an aircraft to enter a heading to follow into a flight management system, which treats the heading as the current leg of a flight plan otherwise being followed by the flight management system. The present invention graphically displays the heading leg as the predicted track so that the pilot is able to see the airplane's expected path. Such a change allows the autopilot to continue following commands from the flight management system rather than being changed to a mode in which the autopilot follows heading commands directly from the pilot.

Abstract: A Real-time Allocation Flight Management System and method, which defines specific roles functions for crew during the implementation of the flight plan. The flight control system requires crew input during pre-programmed way points during the flight. When fully functional, the system can control all aspects of a flight, including attitude and power control as well as all ancillary systems necessary for flight from takeoff to touchdown. In the event that the crew is incapacitated, the system can select the most probable approach procedure in use based on whatever information is available such as current and forecast destination weather, prevailing winds, and approach possibilities, such as available runways. Adjustment of the flight plan trajectory, allows the system to follow the adjusted trajectory. Included is a simulator software program, a free-standing flight simulator and methods of incorporating training protocols for flight crews.

Abstract: A missile has a pair of systems to provide acceleration information during flight. The primary system is a microelectromechanical systems (MEMS) inertial measurement unit (IMU) that provides accurate rate sensor output, such as providing pitch and yaw rates, at low cost, over a wide range of conditions. However MEMS IMUs are susceptible to temporary incorrect responses when subjected to shocks, such as acoustic-range shocks, for instance in the range of 10-20 kHz. The missile includes a secondary system to temporarily provide acceleration data during the periods following shocks, when the MEMS IMU does not provide valid (reliable or usable) rate sensor output, for use in estimating pseudo pitch and yaw rates. The secondary system may be an accelerometer that does not provide navigation-quality acceleration data, but does provide a sufficiently accurate response in order to maintain stable flight during the post-shock period.

Abstract: A method and device are provided for determining a target altitude for an emergency descent of an aircraft that is to be reached by the end of the emergency descent. The method includes determining an initial target altitude representative of the initial position of the aircraft and then repeatedly determining a current target altitude along a reference horizontal distance. The current target altitude is compared to the initial target altitude and is used to update the emergency descent if the current target altitude is lower than the initial target altitude. Each target altitude is selected as the larger of a predetermined threshold altitude and a security altitude that ensures any obstructions along a remaining horizontal distance are avoided.

Abstract: Disclosed is a method and device for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight. The lateral effects are attenuated by applying a roll control order to control a first controllable movable member that acts on aircraft roll and minimizes aircraft roll-wise disturbances due to wind, and a yaw control order that controls a second controllable movable member to act on aircraft yaw. The roll and yaw control orders are calculated based on a sideslip value of the aircraft, while the yaw control order is calculated as a function of the roll control order to compensate for aircraft lateral effects due to turbulence, as well as lateral effects due to application of the roll control order to the first movable member.

Abstract: An apparatus and method for estimating future pitch and roll angles of an aircraft to compensate for a time delay caused by a flight instrumentation system calculating the aircraft's pitch and roll. The apparatus may output signals to an aircraft autopilot system. The apparatus may comprise various inputs and outputs, at least one compensation module, and at least one addition module. The compensation module may multiply a gain value by the pitch rate of the aircraft and by the roll rate of the aircraft to determine a pitch compensation amount and a roll compensation amount. Then the pitch compensation amount may be added to the pitch of the aircraft, and the roll compensation amount may be added to the roll of the aircraft to solve for a compensated pitch and a compensated roll to send to the autopilot system.

Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.

Abstract: This invention relates to an intelligence system on board an aircraft that detects an emergency, assesses the situation, and then acts on the situation in a pre-determined manner.

Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.

Abstract: Systems and methods for planning and executing a search route by a mobile sensor platform for detecting reflection are disclosed. The search route of the mobile sensor platform is based on the angle of a radiation source relative to the ground in a search area. While executing the search route, a sensor on the mobile sensor platform is configured to detect the reflection of radiation from an object in the search area.

Abstract: A system for transporting inventory items includes an inventory holder capable of storing inventory items and a mobile drive unit. The mobile drive unit is capable of moving to a first point with the inventory holder at least one of coupled to and supported by the mobile drive unit. The mobile drive unit is additionally capable of determining a location of the inventory holder and calculating a difference between the location of the inventory holder and the first point. The mobile drive unit is then capable of determining whether the difference is greater than a predetermined tolerance. In response to determining that the difference is greater than the predetermined tolerance, the mobile drive unit is also capable of moving to a second point based on the location of the inventory holder, docking with the inventory holder, and moving the mobile drive unit and the inventory holder to the first point.

Abstract: The present invention is a method for providing optimum multi-map overlay in a flight deck navigation display of an aircraft. The method includes outputting absolute terrain data to the navigation display for display by the navigation display. The method further includes receiving a threshold elevation input, the threshold elevation input including a threshold elevation. The method further includes receiving relative terrain data. The method further includes, when the aircraft is located below the threshold elevation, overlaying the relative terrain data onto the absolute terrain data based on the received threshold elevation input. Further, the absolute terrain data and the relative terrain data are concurrently displayed by the navigation display, the displayed relative terrain data being overlaid onto the displayed absolute terrain data.

Abstract: There is provided a method for identifying, at the moment of verification, the situation of a threat to a protected ground, airspace and/or sea limits by an approaching ground vehicle, aircraft or sea-going vessel. The method includes an authorized driver/pilot/captain to select first state in which the vehicle, aircraft or sea-going vessel is not considered to present a threat and a second state in which the vehicle, aircraft or sea-going vessel is considered to present a threat. The method further provides entering the first and second PIN codes into a smart card for generating a One Time Indicia (OTI) for each of the PIN codes and disclosing the state associated with each of the first and second OTI codes to at least one control center. Upon the control center receiving an OTI code, the control center obtains positive identification of the driver/pilot/captain and the degree of the threat that the vehicle, aircraft or sea-going vessel presents.

Abstract: The fields of the invention are vehicle on-board security and vehicle piloting safety. The invention relates to a method and device for aiding the restoral of command of a vehicle by an operator of the vehicle. The command of the vehicle by the operator is ensured through vehicle piloting controls, when the operator has lost command of the vehicle in favor of a device for disabling piloting controls. The device disables the action of the piloting controls on the piloting means during the loss of command. According to the invention, the method includes emitting a restoral of command request; a vehicle motion phase is determined; a reference state of the piloting control is determined as a function of the motion phase; a current state of the piloting control is determined; the current state with the reference state is compared so as to identify a deviation ? between the current state and the reference state. When no deviation ? is identified, the command of the vehicle by the operator is restored.

Abstract: An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information.

Abstract: An aircraft capable of hovering, and characterized by having at least one sensor, which has a plane sweep region and is designed to acquire, when the aircraft is manoeuvring, values of respective distances between first points on an obstacle within the plane sweep region, and a second point on the aircraft; and a control unit designed to generate an alarm signal when at least one of the first points lies within a safety region containing the second point on the aircraft.

Abstract: A piloting method and device for avoiding pilot induced oscillations filters a piloting order with a non-linear filtering function that is controlled by speed comparison information.

Abstract: Method and device for assisting the piloting of an aircraft. The device (1) comprises means (4) for determining, using a roll instruction and measured current values of external characteristics and of flight characteristics of the aircraft, a predicted path which is a flight path having a constant roll angel, taking account of the effect of the wind.

Abstract: Disclosed are methods and systems that include a method for controlling movement of a first unmanned vehicle (UV) to search an area, where the method includes generating a first trace associated with prior positions in which the first UV has been located, determining a direction in which the first UV is to move using the first generated trace, and causing the first UV to move in the determined direction. The trace may be a numerical value that decreases as a function of the time that has elapsed since the first trace was generated. The methods and systems may also include receiving data relating to a second trace, and using that second trace to determine the direction. The second trace may be generated by a second UV. The second trace may be associated with a position within a predetermined radius from a position associated with the first UV.

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 method and device automatically engage an emergency descent function of an aircraft as a function of pressure variation measured in the cabin of the aircraft.

Abstract: Unmanned aerial vehicle take-off and landing systems are disclosed herein. In one embodiment, a method of landing an unmanned aerial vehicle includes programming a landing location for the unmanned aerial vehicle utilizing a user input device. The unmanned aerial vehicle is launched. Communications between the unmanned aerial vehicle and the user input device are interrupted, and the unmanned aerial vehicle is landed at the landing location based on the programmed landing location and not based on any real-time communication between the unmanned aerial vehicle and the user input device.

Abstract: An unmanned aerial vehicle variable autonomy control system is disclosed. In one embodiment, the system includes a control mode interface that provides a plurality of selectable control modes for an unmanned aerial vehicle, wherein one of the plurality of selectable control modes comprises an autonomous landing mode. Also included is a route editing interface that, following a selection of the autonomous landing mode, facilitates a receipt of an input indicative of a landing location. The system also includes a communications component that transmits a command to the unmanned aerial vehicle, wherein the command is based at least in part on the input indicative of the landing location.

Abstract: A vehicle guidance system comprising: a measurement system; a processor arranged to receive information from the measurement system and convert said information into at least one time-to-contact based parameter; and a control system arranged to receive the at least one time-to-contact based parameter from the processor and use the at least one time-to-contact based parameter to either automatically guide the vehicle or to provide vehicle guidance information to a pilot.

Abstract: An on-board diagnostic system of a vehicle comprises disabling diagnostic operation, such as a misfire monitor, based on road roughness. In one example, the disabling of the diagnostic operation is based on brake actuation and degradation of an anti-lock braking system.

Abstract: The present invention relates to a friction device (11) for maintaining a control member (2, 8) in a determined position. The device comprises a contact part (16) movable between a declutched stable position and a clutched stable position, and vice versa. The clutched stable position corresponds to a position in which the contact part (16) bears against the control member (2, 8) in such a manner as to establish a determined friction force. An electromechanical drive means moves the contact part (16) between the two stable positions. The device includes remote control means for activating and deactivating the drive means.

Abstract: A range estimation device for use in an aerial platform including at least one passive sensor, a trajectory determination unit and a control system. A control unit is arranged to indicate to the control system to perform own-ship maneuvering of the aerial platform such that characteristics of passive sensor measurements from the at least one passive sensor enable a range estimation to a target to be determined. The control unit is arranged to determine characteristics of the own-ship maneuvering based on the range uncertainty estimations to the target. A method and a computer program product for use in range estimation device.

Abstract: A watercraft steering device can include at least one of steerage status detection device configured to detect a steerage status following an operation of the steering wheel, running status detecting device configured to detect a running status of the watercraft, watercraft propulsion unit status recognition device configured to recognize a status of an outboard motor such as an installation number thereof, and electric motor status detection device configured to detect a status of an electric motor, and can further include a lower unit turning force characteristic computation device configured to compute a lower unit turning force characteristic based on a detection value from at least one of the device, and an ECU configured to control at least one of a reaction force to the steering wheel, a limit lower unit turning angle, and a propulsive force based on a computed lower unit turning force characteristic and/or selecting the electric actuator to operate.

Abstract: An aircraft piloting method and device for picking up a vertical profile of a flight plan. The device combines a manual piloting device that enables a pilot to control the start of the picking-up of a vertical profile and an automatic piloting device for automatically ending the vertical profile picking-up and following the vertical profile.

Abstract: Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information are disclosed. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.

Abstract: A device and method for assisting in the management of an engine failure on an aircraft: (1) determine, when an engine failure occurs, flight profiles allowing the closest airports to be reached according to flight strategies and (2) present, on a screen, the airports associated with the determined flight profiles and corresponding predictions.

Abstract: A control device for controlling a controlled system, such as steering, braking or accelerating when driving a car, as well other operations for other vehicles or systems, includes an automatic control system that generates automatically generated control signals, a haptic control command input device generates manual control command inputs, and an arbitration unit which resolves disputes between the automatically generated signals and the manual control command inputs. The haptic control generates control signals that depend on both the automatically generated control signals and the manual control command inputs, and adjustments are made continuously therebetween using rule based feed back control signals. Arbitration is performed in the dead spaced of the controlled system or the haptic control command input device.

Abstract: The invention relates to a method for producing an audible warning when an aircraft autopilot is deactivated. The method includes a) transmitting a first sound in the aircraft cockpit during a time ranging from a first predetermined value and a second predetermined value and b) transmitting a second sound in the aircraft cockpit. The invention also relates to an audible warning device having a monitoring unit for monitoring the deactivation of the aircraft autopilot and an activation unit for emitting an audible warning in the cockpit, where the activation unit is constructed such that it activates the first sound emission whose length ranges from the first predetermined value and a second predetermined value and a second sound when the monitoring unit detects the deactivation of the autopilot.

Abstract: A method for policing and managing the operation of a flying, unmanned aircraft in the event of usurpation of control of, malfunction of, or ill-intentioned use of, this aircraft includes the steps of (a) detecting inappropriate operation of the aircraft; (b) transmitting a takeover command to the aircraft to interrupt control of the operation of this aircraft by a first pilot and relinquish control of the aircraft to a second pilot; and (c) transmitting control commands to the aircraft to control its operation by the second pilot, until the need for alternate pilot control of the aircraft has ended or until the aircraft has landed safely.

Abstract: Unmanned aerial vehicle take-off and landing systems are disclosed herein. In one embodiment, a method of landing an unmanned aerial vehicle includes programming a landing location for the unmanned aerial vehicle utilizing a user input device. The unmanned aerial vehicle is launched. Communications between the unmanned aerial vehicle and the user input device are interrupted, and the unmanned aerial vehicle is landed at the landing location based on the programmed landing location and not based on any real-time communication between the unmanned aerial vehicle and the user input device.

Abstract: Apparatuses and methods for controlling autoflight systems are disclosed herein. An apparatus for use with an aircraft having an autoflight system can include an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes. The autoflight performance selector has at least a first selection and a second selection different than the first selection. Selecting the first selection causes the response of the autoflight system to flight guidance instructions to not exceed a first level in the at least two axes, and selecting the second selection causes the response of the autoflight system to the flight guidance instructions to not exceed a second level in the at least two axes different than the first level.

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract: A system determines a limit angle of climb corresponding to a climb angle of an aircraft for flying over the ground along an avoidance path and displays a characteristic sign representing the limit angle of climb on a display screen.

Abstract: A method for estimating inertial acceleration bias errors including obtaining uncorrected acceleration measurements on board a vehicle; obtaining independent position and independent velocity data of the vehicle; transforming the uncorrected acceleration measurements into a reference frame of the independent position and independent velocity data; blending the transformed acceleration measurements with the independent position and the independent velocity data to produce feedback errors; transforming the feedback errors into the reference frame of the acceleration measurements; multiplying the feedback errors by a gain and integrating to estimate the acceleration measurement bias errors.

Abstract: A self-contained avionics sensing and flight control system is provided for an unmanned aerial vehicle (UAV). The system includes sensors for sensing flight control parameters and surveillance parameters, and a Global Positioning System (GPS) receiver. Flight control parameters and location signals are processed to generate flight control signals. A Field Programmable Gate Array (FPGA) is configured to provide a look-up table storing sets of values with each set being associated with a servo mechanism mounted on the UAV and with each value in each set indicating a unique duty cycle for the servo mechanism associated therewith. Each value in each set is further indexed to a bit position indicative of a unique percentage of a maximum duty cycle for the servo mechanism associated therewith. The FPGA is further configured to provide a plurality of pulse width modulation (PWM) generators coupled to the look-up table. Each PWM generator is associated with and adapted to be coupled to one of the servo mechanisms.