Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.

Abstract: An autonomous control method autonomously controls a small unmanned helicopter toward target values, such as a set position and velocity, by deriving model formulas well suited for the autonomous control of small unmanned helicopters, by designing an autonomous control algorithm based on the model formulas, and by calculating the autonomous control algorithm. The autonomous control system includes sensors that detect current position, attitude angle, altitude relative to the ground, and absolute azimuth of a nose of the small unmanned helicopter; a primary computational unit that calculates optimal control reference values for driving the helicopter from a target position or velocity values; a secondary computational unit that converts data collected by the sensors and the computational results as numeric values that are output by the primary computational unit into pulse signals; a ground station host computer used as the computational unit for the autonomous control system; and so on.

Abstract: The information relates to a method of transmitting information between a communications management unit on board an aircraft and a ground air control system, characterized in that it comprises the following steps consisting, in respect of the communications management unit, in: a) detecting the reception of alerts originating from an onboard surveillance system, via a communication bus, b) when an alert is detected, shaping the information contained in the alert as a report according to a predetermined format, and dispatching this report to the ground system.

Abstract: A fly-by-wire (FBW) system (104) is coupled to cockpit controls (102) of an aircraft for controlling the aircraft, and an automatic flight control system (AFCS) (108) is coupled to the FBW system for maintaining the aircraft in stable flight. An unauthorized-flight detector (110) is coupled to the FBW system and coupled to the AFCS, and is arranged to carry out (306) a transfer of partial control of the aircraft from the cockpit controls to the FBW system and the AFCS, in response to a predetermined event.

Abstract: Methods, systems, and products are provided for enabling services on a UAV. Embodiments include determining a current position of the UAV, selecting a service module for the UAV in dependence upon the current position of the UAV, uploading the service module to the UAV, and executing the service module on the UAV. Selecting a service module for the UAV in dependence upon the current position of the UAV may include retrieving from a module database a module record in dependence upon the current position of the UAV. Typical embodiments also include selecting a flying pattern algorithm in dependence upon the selected service module and piloting the UAV in accordance with the flying pattern algorithm. Many embodiments also include selecting a navigational algorithm in dependence upon the selected service module and navigating the UAV in accordance with the navigational algorithm.

Abstract: Methods and systems for handling aircraft control information are disclosed. A system in accordance with one embodiment of the invention includes a display medium coupleable to a flight manager, with the flight manager configured to receive and direct instructions for automatically controlling aircraft functions at a future time during flight of the aircraft. The system can further include a display controller coupled to the display medium to present at least one operator activatable element at the display medium and update information presented at the display medium when the operator activates the operator activatable element. For example, the operator activatable element can include an icon presented at a computer display screen, and can be activated by a keystroke.

Abstract: A method for operating an aircraft includes the steps of receiving guidance instructions and guidance parameters at a navigation computer, and transmitting automatic pilot instructions from the navigation computer to a flight control computer. The method also includes the steps of receiving control instructions and the automatic pilot instructions at the flight control computer, and generating operating commands at the flight control computer. In an automatic pilot mode, the operating commands are generated at the flight control computer based on the automatic pilot instructions.

Abstract: The GPS (Global Positioning System) Autopilot System utilizes approximately fourteen (14) to twenty-four (24) microprocessors, depending on the size of the aircraft. These microprocessors computer control fuel and airspeed, ailerons, elevators, rudder and breaking automatically by following pre-programmed GPS fixes stored in the aircraft's onboard GPS database, and making the required mechanical system adjustments so that the real-time GPS fixes become the virtual GPS fixes when the aircraft moves. The GPS database is programmed during an identical flight plan, flown by an experienced pilot. During this flight, GPS coordinates and UTC time is recorded and stored in GPS database. All the stored GPS coordinates or fixes can be used or a portion of the flight fixes can be used, such as just the approach and landing sequence of GPS fixes.

Abstract: A device and method for assisting in the management of an engine failure on an aircraft. The device (1) comprises means (7) for determining, when an engine failure occurs, flight profiles allowing the closest airports to be reached according to flight strategies, and means (13) for presenting, on a screen (13A), the airports associated with certain of said flight profiles, together with corresponding predictions.

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: The present invention relates to a method of generating instruction values for servo-controlling a flight parameter P of an aircraft equipped with an automatic pilot, between a current value C and a target value T. It comprises a phase for determining increasing or decreasing instruction values PC of the flight parameter P and instruction values ( ? P ? t ) C of its time derivative and/or (?Pdt)C of its integral. It also comprises a phase of use, by a servo-control law of the parameter P of the automatic pilot, of each of the instruction values PC, ( ? P ? t ) C and/or (?Pdt)C. It also comprises a phase of use, by the automatic pilot, of the value T as final target value. The instruction values PC, ( ? P ? t ) C and/or (?Pdt)C are calculated from the current value C, the target value T of the parameter P and a time constant ?.

Abstract: A security mechanism identifies users, so as to restrict access and operation to authorized users, such as to persons authorized to access and fly a particular aircraft. The security mechanism comprises one or more security devices to identify the user attempting to gain access or operate the controller; and one or more monitoring devices to determine whether or not the user identified is authorized to have access or operate the controller. Methods of safely operating aircraft are also described. The methods include protocols for limiting access to the aircraft and assuming remote control of the aircraft if a possibly hostile situation is detected.

Abstract: A method of automatically guiding an aircraft for flight at low altitude determines an LLF (low level flight) trajectory section for following terrain to be overflown by the aircraft. The LLF trajectory section takes account of predictions of the aircraft's mass and speed and climb and descent performance. The LLF trajectory section includes an entry point and an exit point. The LLF trajectory section is integrated between a first trajectory part corresponding to a first phase of flight and a second trajectory part corresponding to a second phase of flight, by providing respectively first and second transition phases. The aircraft is automatically guided so that it successively captures, follows, and leaves the LLF trajectory section.

Abstract: A device for adjusting a parameter includes a selector that is actuated by an operator. A coder is driven in rotation by the actuation of the selector and emits a signal representative of the rotation. A first detector detects an actuation of the selector, and a second detector detects the emission of the signal indicating the change of the selected value. A comparitor, linked to the first and second detectors, determines a malfunction when only one of the first and second detectors makes a detection.

Abstract: An emergency flight plan useable for an aircraft provided with a navigation system wherein the flight plan includes a pointer matrix including a number of cells. Each cell of the matrix has a unique identification and each cell corresponds to a geographical area, and wherein each cell of the matrix includes an identification of a cell corresponding to a next waypoint in an emergency route.

Abstract: A method of creating a termination map for an aircraft over an area of interest indicating the lowest allowable flight altitude to achieve a glide path of a vehicle to a termination point of the area of interest and a map of vectors of the area of interest indicating direction towards a termination point to control an unmanned vehicle.

Abstract: Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing.

Abstract: A system and method for operating an aircraft such that any hostile persons taking over the cockpit, for instance, terrorists or a disgruntled pilot, cannot control the flight path of the aircraft to enter restricted airspace, such as ‘no fly’ zones, or any authorized pilots while operating an aircraft cannot unintentionally enter any no fly zone areas.

Abstract: A security mechanism identifies users, so as to restrict access and operation to authorized users, such as to persons authorized to access and fly a particular aircraft. The security mechanism comprises one or more security devices to identify the user attempting to gain access or operate the controller; and one or more monitoring devices to determine whether or not the user identified is authorized to have access or operate the controller. Methods of safely operating aircraft are also described. The methods include protocols for limiting access to the aircraft and assuming remote control of the aircraft if a possibly hostile situation is detected.

Abstract: Embodiments are disclosed for a vehicle control system and related sub-components that together provide an operator with a plurality of specific modes of operation, wherein various modes of operation incorporate different levels of autonomous control. Through a control user interface, an operator can move between certain modes of control even after vehicle deployment. Specialized autopilot system components and methods are employed to ensure smooth transitions between control modes. Empowered by the multi-modal control system, an operator can even manage multiple vehicles simultaneously.

Abstract: This invention relates to a safety system for aircraft, wherein prohibited airspaces which aircraft may not enter are marked on a digitally stored image of the airspace, wherein the aircraft is provided with an automatic control device that automatically steers the aircraft on to an alternative route, which is situated outside the prohibited airspace, when the probability that the aircraft will enter the prohibited airspace exceeds a predetermined threshold value.

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: A flight instrument and associated method where vertical speed information is combined with gyro information to produce gyro enhanced vertical speed information that is displayed to a pilot. The gyro information may include a pitch rate gyro and may include an azimuth rate gyro. The pitch rate gyro and azimuth rate gyro may be combined to yield a corrected pitch rate in turns. In one embodiment, the display is an airplane symbol that moves relative to a horizon line responsive to the gyro enhanced vertical speed information. The horizon line may also tilt in response to the azimuth rate gyro.

Abstract: A system and method for providing autonomous control of unmanned aerial vehicles (UAVs) is disclosed. The system includes a ground station in communication with an unmanned aerial vehicle. The method for providing autonomous control of a UAV includes methods for processing communications between the ground station and UAV. The method also includes procedures for processing commands from the ground station. Also included in the method is a process for estimating the attitude of the UAV and autonomously maintaining its altitude within a desired threshold. The method also includes a process for autonomously orbiting about a specified point in space. Combined with these processes, the method also includes a process for an autonomous takeoff and landing of the UAV.

Abstract: A vehicle operator condition monitoring system is provided. In one embodiment, the vehicle condition monitoring system includes a physical condition monitoring unit such as a camera, a data processing system, a navigation system, and a communication system. The physical condition monitoring unit is mounted in a vehicle to monitor at least one physical trait of a vehicle operator. The data processing system is coupled to the physical condition monitoring unit to compare data acquired by the physical condition monitoring unit with rules indicating types of action to be taken. The navigation system is functionally coupled to the data processing system allowing the data processing system to determine the location of the vehicle and the communications system is functionally coupled to the data processing system to allow the data processing system to contact an appropriate entity should the physical condition of the vehicle operator warrant such contact.

Abstract: Navigating a UAV, including receiving in a remote control device a user's selection of a GUI map pixel that represents a waypoint for UAV navigation, the pixel having a location on the GUI; mapping the pixel's location on the GUI to Earth coordinates of the waypoint; receiving downlink telemetry, including a starting position from a GPS receiver on the UAV, from the UAV through a socket on the remote control device; calculating a heading in dependence upon the starting position, the coordinates of the waypoint, and a navigation algorithm; identifying flight control instructions for flying the UAV on the heading; and transmitting uplink telemetry, including the flight control instructions, through the socket to the UAV. In some embodiments the UAV is piloted, under control of a navigation computer on the UAV, from the starting position to the waypoint in accordance with a navigation algorithm.

Abstract: A pilot seat ejection system for use in a number of environments, can be designated for automatic operation. A microprocessor, or other on-board computer, uses avionic sensors to sense an irreversible catastrophic or dangerous situation, thereby initiating automatic ejection. While the system is particularly applicable during vertical operation of an STOVL Aircraft, the present system can be used on a wide variety of different vehicles in a wide variety of different situations.

Abstract: A recording of a macro is initiated. A first of a plurality of actions performable by the moveable barrier operator is selected and the first action is associated with the macro. At least a second of the plurality of actions available is selected at the moveable barrier operator and the second action is associated with the macro. A functional sequence of the first and second actions is recorded. The functional sequence specifies the order of performance of the first and second action. The recording of the macro is terminated. Subsequent to the terminating, actions recorded by the macro are performed at the moveable barrier operator in accordance with the functional sequence.

Abstract: A system for operating an aircraft includes a navigation computer and a flight control computer. The navigation computer receives guidance instructions and guidance parameters, and outputs automatic pilot instructions. The flight control computer receives control instructions and the automatic pilot instructions, and generates operating commands based on the automatic pilot instructions in an automatic pilot mode.

Abstract: A method for maintaining a position of a hovering vehicle that incorporates a radar altimeter is described. The method includes receiving signals at the radar altimeter based on a change of horizontal direction, operating the radar altimeter to generate a Doppler frequency spectrum based on the received signals, and determining a change in vehicle direction and velocity which will reduce a width of the Doppler frequency spectrum of the received signals. A radar altimeter which generates the Doppler frequency spectrum is also described.

Abstract: Measurement of a spatial velocity vector in order to make determination of a geographical position possible. A spatial velocity meter includes an inertial measurement unit, a direction-sensing module and a velocity processor. The inertial measurement unit registers acceleration parameters and angular velocity parameters in three dimensions. The direction-sensing module registers a natural reference signal. The velocity processor receives the acceleration parameters, the angular velocity parameters and the natural reference signal, and based thereon, generates the spatial velocity vector.

Abstract: A method and device for detecting pilot induced oscillations in an aircraft may detect signals having frequencies of between 0.3 Hz and 0.6 Hz within commands signals generated by a pilot for controlling an aerodynamic surface of the aircraft. The energy of the detected signals is analyzed to determine whether significant pilot induced oscillations are present within the command signals, and an indication of the degree of the oscillations is generated for use by the pilot.

Abstract: A flight control system for preventing an aircraft colliding with designated man-made structures in which the geographical position of the aircraft is determined and then compared with predetermined geographical boundaries that represent excluded zones; these zones being defined around the man-made structures; where the system, as appropriate, overrides a normal flight control system (such as a fly-by-wire flight system) to alter the course of the aircraft to avoid all excluded zones, irrespective of any pilot commands.

Abstract: An avionics system having displays with display configurations pilot selected for a phase of flight of an aircraft and reconfigurable for each phase of flight. A multifunction flight display stores and displays the stored phase of flight display configurations for each phase of flight of the aircraft. A cursor control panel connected to the multifunction display for changes from one stored phase of flight display configuration to another stored phase of flight display configuration when the aircraft changes phase of flight. The cursor control panel also is used for reconfiguring the display configuration for each phase of flight. The cursor control panel has phase of flight quick access pushbuttons for selecting a stored phase of flight configuration and for reconfiguring a stored phase of flight configuration into a new phase of flight configuration by selecting the new configuration and pressing a phase of flight quick access pushbutton for a predetermined time to store the new configuration.

Abstract: Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information. 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: The present invention is a computer system designed to use the conventional devices and special programming of the present invention that will ensure the safe operation of aircraft. The present invention is an anti-terrorist and Anti-Crash System to ensure and maintain complete control of an aircraft on the ground, during taxiing and even in the air. With the present invention in place, an aircraft can be kept a safe distance from any building and other aircraft, and the aircraft can be remotely controlled. The system provides greater national security. Utilizing the On-Demand audio and visual monitoring components of the present invention, simultaneously, proper authorities can access all factual data from all onboard flight systems before a crash is imminent. Equipment lockouts are in place as well, so that if an aircraft is commandeered, the actual person in the cockpit is unable to effect aircraft travel, virtually eliminating human error.

Abstract: A monitoring and control system for manned vehicles is being proposed, wherein an automatic early-on recognition of emergencies and an automatic specification of measures to be taken in accordance with a separate escalation assessment concerning the development of the emergency in question are made possible, in that data packets comprising a vehicle identification field, a time indicator field, a continuously updated position field, a continuously updated vehicle-status field and a pilot-confirmation field are either transmitted from the vehicle to a ground station and evaluated there or is transmitted to the ground station already having been evaluated, wherein continuous storing of the data packets is carried out over a limited period of time in the ground station when a first evaluation result is present; in the event of the occurrence of a second particular evaluation result storing is carried out over a longer period of time and at the same time a switchover signal is transmitted to the vehicle, which sw

Abstract: A virtual sensor mast for a ground vehicle and a method for operating a ground vehicle using a virtual sensor mast are disclosed. The virtual sensor mast includes an unmanned airborne vehicle capable of lifting itself from the ground vehicle upon deployment therefrom; a sensor suite mounted to the unmanned airborne vehicle; and a tether between the unmanned airborne vehicle and the ground vehicle over which the sensor suite is capable of communicating sensed data upon deployment. The method includes elevating a tethered unmanned airborne vehicle from the ground vehicle to a predetermined height; sensing environmental conditions surrounding the ground vehicle; and terminating the deployment.

Abstract: A security enhanced automatic pilot system for an air vehicle. Upon a change of trajectory for an air vehicle during flight, the pilot is requested to confirm the change in trajectory. Through the placement of the pilot's finger on a fingerprint sensor, messages can be sent regarding the reason for the trajectory change. A first finger can represent a normal message, whereas a second message can represent a security message. Where a security message is sent, the automatic pilot system can automatically direct the air vehicle to a predetermined flight path.

Abstract: This MCP/FCU interface (30) for control of the automatic pilot (13) and/or flight director (14) is provided with an access port linked to the ATN terminal (2) by a digital information transmission link (4) and furnished with display device displaying the trajectory modification orders originating from the air traffic control authorities and with enabling device imposing on the automatic pilot (13) and/or flight director (14) the operating mode and the directives corresponding to a trajectory modification order having formed the subject of an acceptance by the pilot.

Abstract: Methods and systems for performing auto-recovery for an aircraft. An example system includes position and information systems, an automatic flight control system, a database, and a processor. The database includes terrain data, airport data, obstacle data, and protected airspace data. The processor determines if one of a caution alert or a warning alert exists based on data stored in the database and information received from the position and information systems. Auto-recovery instructions are generated and sent to the automatic flight control system if no positive flight control input has been performed at time of expiration of a waiting period. Auto-recovery instructions are generated based on an analysis of two or more auto-recovery routes. The system does not perform auto-recovery if components of the system fail to meet a predefined validity or integrity level.

Abstract: A remote control signal, such as a signal from a GPS satellite or from an escort aircraft, is received at a servant aircraft. If the remote control signal is valid and is a landing remote control signal, the processor causes the landing of the servant aircraft. The processor may cause a crash landing or a landing at an airport.

Abstract: A system and method are provided for precisely adjusting individual aircraft airspeed system in order to provide more accurate cruise Indicated Airspeed (IAS). The system includes a flight data computer, an autopilot, and airspeed displays. The flight data computer includes a first component that records in-service data to determine actual fuel mileage for the aircraft for comparison to a production rating fuel mileage. The flight data computer also includes a user interface that allows a user to set a Mach trim value based on the comparison and a third component that adjusts indicated airspeed based on the determined Mach trim value. The autopilot and airspeed displays receive the adjusted indicated airspeed.

Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

Abstract: A relatively low cost but effective vehicular safety system includes a navigational status determination system generating navigational status information, an alarm response system generating alarm responses in response to alarm response command information and a data processing system. The data processing system stores a list of safety zones having one or more safety conditions for each safety zone. The data processing system receives the navigational status information and compares the received navigational status information to the stored safety conditions. If a safety condition is found to be violated the data processing system communicates a response command to the alarm response system. Depending upon the severity of the violated safety condition, the alarm response system notifies the vehicle operator of the violation, notifies law enforcement authorities external to the vehicle of the violation or takes some other safety response.

Abstract: Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by the thrust generators is defined. Using the balance as restricting condition, propeller thrusts of the thrust generators and rudder angles and changing speeds of rudders that minimize the performance index are calculated.

Abstract: The piloting system (1) for generating orders for piloting the aircraft according to at least one piloting axis, for example the pitch axis, the roll axis, the yaw axis or the engine thrust control axis, comprises at least two piloting means (2, 3), each of which is capable of calculating the derivative with respect to time of the function which represents the corresponding piloting law and which takes into account the current values of parameters of the aircraft, first means (4) for intercomparing the derivatives calculated by the piloting means (2, 3) and for selecting a derivative; and second means (10) for integrating a selected derivative in such a way as to obtain said piloting order according to said piloting axis.

Abstract: A system and method which partitions a parameter estimation model, a fault detection model, and a fault classification model for a process surveillance scheme into two or more coordinated submodels together providing improved diagnostic decision making for at least one determined operating mode of an asset.

Abstract: A system and method for monitoring an apparatus or process asset including creating a process model comprised of a plurality of process submodels each correlative to at least one training data subset partitioned from an unpartitioned training data set and each having an operating mode associated thereto; acquiring a set of observed signal data values from the asset; determining an operating mode of the asset for the set of observed signal data values; selecting a process submodel from the process model as a function of the determined operating mode of the asset; calculating a set of estimated signal data values from the selected process submodel for the determined operating mode; and determining asset status as a function of the calculated set of estimated signal data values for providing asset surveillance and/or control.

Abstract: Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.