Abstract: An automatic take-off and landing control device for an aircraft is provided. The control device comprises at least two of at least one local tracking device adapted for receiving at least one local signal from at least one local ground station and for determining a position of the aircraft based on the local signals, at least one GNSS tracking device adapted for receiving a GNSS signal and for determining a position of the aircraft based on the GNSS signal; and at least one camera device adapted for observing an environment of the aircraft and for determining a position of the aircraft based on the camera signal.

Abstract: An aircraft navigation system and navigation method. The system comprises a civil-certified GPS-receiver for determining first position information based on C/A-GPS-signals, and a military-type GPS-receiver for determining a second position information based on P(Y)-GPS-signals. A monitoring unit detects a first abnormal condition during jamming conditions within the C/A-GPS-signals. The unit compares the first position information with the second position information and detects a second abnormal condition when a difference between these position information is larger than a threshold value for more than a threshold duration. Upon detecting an abnormal condition, an alert procedure is initiated. In remotely piloted aircraft, Command & Control link-loss is also monitored and during link-loss, a transponder code automatically indicates communication failure.

Abstract: An automatic landing system contains a control device for providing positional data for controlling an aircraft, a first position or range measuring device for detecting first positional data of the aircraft, a second position or range measuring device for detecting second positional data of the aircraft, and a sensor device for detecting sensor data from which a direction in which a landmark is located and/or a distance of the landmark to the aircraft can be determined. The control device may be configured to generate, based on the first positional data, a first hypothesis for the direction and distance of the landmark and, based on the second positional data, a second hypothesis for the direction and distance of the landmark. Moreover, the control device may be configure to confirm or discard the first hypothesis and the second hypothesis, respectively, using the sensor data detected by the sensor device.

Abstract: A control and/or management system for a vehicle includes at least one of: (A) at least two redundant vehicle management computers configured to generate system control commands for each maneuvering actuators and for each system actor based on the data acquired by the sensors; (B) at least two redundant remote interface units for interconnecting a sensor or a system actor with a vehicle management computer; (C) at least two redundant actuator control computers configured to generate control commands for each maneuvering actuator based on received maneuvering commands; and (D) a common interface for connecting an external computer, the common interface being directly connected to at least two redundant computers.

Abstract: An aircraft navigation system and navigation method. The system comprises a civil-certified GPS-receiver for determining first position information based on C/A-GPS-signals, and a military-type GPS-receiver for determining a second position information based on P(Y)-GPS-signals. A monitoring unit detects a first abnormal condition during jamming conditions within the C/A-GPS-signals. The unit compares the first position information with the second position information and detects a second abnormal condition when a difference between these position information is larger than a threshold value for more than a threshold duration. Upon detecting an abnormal condition, an alert procedure is initiated. In remotely piloted aircraft, Command & Control link-loss is also monitored and during link-loss, a transponder code automatically indicates communication failure.

Abstract: An aircraft fuel system comprises a fuselage tank and wing fuel tanks each connected to the fuselage fuel tank by a respective fuel line. A first fuel line connects the fuselage fuel tank to a collector fuel tank, which is connected by second fuel lines to aircraft engines in use of the system. Unspent fuel output from the aircraft engines is returned to the collector fuel tank via third fuel lines. A fuel line arrangement is arranged to draw fuel from, and return that fuel to, the wing fuel tanks. Fuel within the third fuel lines is thermally coupled to fuel within the fuel line arrangement by a heat exchanger. Heat energy within unspent fuel output from the aircraft engines is transferred to the wing fuel tanks, reducing the likelihood of fuel freezing within these tanks during extended flying in cold environments.

Abstract: A method for an aircraft for handling potential collisions in air traffic includes providing by a collision avoidance system a collision avoidance maneuver to avoid a collision with one or more intruders. The collision avoidance system is configured to obtain information about these intruders. The method includes further providing flight management constraints from an onboard flight system. Further, the method includes providing flight situation data from a navigation system. The method includes generating a modified collision avoidance maneuver based on the collision avoidance maneuver provided by the collision avoidance system, the flight situation data and the flight management constraints.

Abstract: A method for autonomous controlling of an aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of: measuring flight and/or system data of the aerial vehicle; performing an evaluation of a flight condition of the aerial vehicle based on the measured data and based on at least one decision criterion; and, issuing at least one autonomous controlling command, if, as a result of the evaluation of the flight condition, the aerial vehicle is in danger.

Abstract: A method for autonomous controlling of a remote controlled aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of: initializing a data link between the aerial vehicle and a ground segment; determining an operation condition of the data link during use of the data link; and issuing at least one autonomous controlling command, if, as a result of the determining, a loss of the data link is determined.

Abstract: An automatic take-off and landing control device for an aircraft is provided. The control device comprises at least two of at least one local tracking device adapted for receiving at least one local signal from at least one local ground station and for determining a position of the aircraft based on the local signals, at least one GNSS tracking device adapted for receiving a GNSS signal and for determining a position of the aircraft based on the GNSS signal; and at least one camera device adapted for observing an environment of the aircraft and for determining a position of the aircraft based on the camera signal.

Abstract: An automatic landing system contains a control device for providing positional data for controlling an aircraft, a first position or range measuring device for detecting first positional data of the aircraft, a second position or range measuring device for detecting second positional data of the aircraft, and a sensor device for detecting sensor data from which a direction in which a landmark is located and/or a distance of the landmark to the aircraft can be determined. The control device may be configured to generate, based on the first positional data, a first hypothesis for the direction and distance of the landmark and, based on the second positional data, a second hypothesis for the direction and distance of the landmark. Moreover, the control device may be configure to confirm or discard the first hypothesis and the second hypothesis, respectively, using the sensor data detected by the sensor device.

Abstract: A control and/or management system for a vehicle includes at least one of: (A) at least two redundant vehicle management computers configured to generate system control commands for each maneuvering actuators and for each system actor based on the data acquired by the sensors; (B) at least two redundant remote interface units for interconnecting a sensor or a system actor with a vehicle management computer; (C) at least two redundant actuator control computers configured to generate control commands for each maneuvering actuator based on received maneuvering commands; and (D) a common interface for connecting an external computer, the common interface being directly connected to at least two redundant computers.

Abstract: A process and system for the planning a cost-minimized aircraft flight route between a starting point and end point takes into account costs associated with the flight route, no-fly zones and flight corridors, and aircraft limitations. A raster set is determined which comprises topographical points between the starting and end points, and costs associated with the respective raster points are determined. N nodes are determined for each raster point of at least one subset of the raster set, such nodes being associated with approach directions of the raster point by the aircraft. Possible take-off directions of the raster point are defined, taking into account the minimum turning radius of the aircraft, as a function of the approach direction. A cost-minimized flight route is determined by means of a shortest path algorithm, taking into account only the k most cost-effective nodes (k<N) for a raster point.

Abstract: A process for determining a route along more than two mutually consecutive preset path points with given connecting routes in-between. In this case, a plurality of connecting routes is given between at least one pair of two mutually consecutive path points. Respective costs and preferably also a respective time duration are assigned to each connecting route. In a first step of the process, a tree is generated which comprises edges and nodes connected by edges. Each node is assigned to a defined path point and each edge corresponds to a connecting route. The route is determined based on a selection of edges of the tree.

Abstract: A process for determining a route along more than two mutually consecutive preset path points with given connecting routes in-between. In this case, a plurality of connecting routes is given between at least one pair of two mutually consecutive path points. Respective costs and preferably also a respective time duration are assigned to each connecting route. In a first step of the process, a tree is generated which comprises edges and nodes connected by edges. Each node is assigned to a defined path point and each edge corresponds to a connecting route. The route is determined based on a selection of edges of the tree.

Abstract: A process and system for the planning a cost-minimized aircraft flight route between a starting point and end point takes into account costs associated with the flight route, no-fly zones and flight corridors, and aircraft limitations. A raster set is determined which comprises topographical points between the starting and end points, and costs associated with the respective raster points are determined. N nodes are determined for each raster point of at least one subset of the raster set, such nodes being associated with approach directions of the raster point by the aircraft. Possible take-off directions of the raster point are defined, taking into account the minimum turning radius of the aircraft, as a function of the approach direction. A cost-minimized flight route is determined by means of a shortest path algorithm, taking into account only the k most cost-effective nodes (k<N) for a raster point.

Abstract: Method provided for implementation in a data processing device for monitoring a permissible integrity of a measured variable of a dynamic system with the steps: Determination of at least one measurement series with respectively one number (n) of measurements (zk) by means of at least one sensor device with respectively one predetermined measuring accuracy (?zk) and a predetermined actual sensor integrity ({1?pk}) related thereto, determination of a number (m) of measuring errors as a function of the actual sensor integrities ({1?pk}), as a function of the number (n) of measurements and as a function of a minimum integrity ({1?p0}), assignment of the determined accuracy range to an accuracy measurement, comparison of the determined accuracy measurement with a threshold value, and issuing a warning as soon as a desired value has been reached, fallen below or exceeded.

Abstract: A method and apparatus for planning vehicle trajectories or routing in which a first optimized route between a starting point and a destination is established with regard to a first, relatively coarse node grid, using known techniques. In order to further refine route selection, a second relatively finer node grid is then established within a predeterminable area or volume that is adjacent yo the first optimized route, along its length. The latter finer node grid is then used to establish a second enhanced polygonal path from among the possible polygonal paths between the starting and destination points according to the finer node grid, once again using a known optimization technique.

Abstract: Flight path planning device for determining path guidance specifications for at least one parachute or paraglider (5), which determines an altitude/time corridor (20, 30) as a flying range to be maintained by the parachute or paraglider (5) or an altitude/timeline (28) as a desired specification, the limits of which are formed from altitude/timelines (22, 24; 31, 32) on the basis of a reference point determined by an altitude and a time coordinate, whereby the course of the altitude/timelines is formed respectively from the integral of a predetermined sink rate (v)/time and whereby different sink rates are assigned to the altitude/timelines, and a path guidance system for determining control specifications for controlling the parachute or paraglider.

Abstract: Method provided for implementation in a data processing device for monitoring a permissible integrity of a measured variable of a dynamic system with the steps: Determination of at least one measurement series with respectively one number (n) of measurements (zk) by means of at least one sensor device with respectively one predetermined measuring accuracy (?zk) and a predetermined actual sensor integrity ({1?pk}) related thereto, determination of a number (m) of measuring errors as a function of the actual sensor integrities ({1?pk}), as a function of the number (n) of measurements and as a function of a minimum integrity ({1?p0}), assignment of the determined accuracy range to an accuracy measurement, comparison of the determined accuracy measurement with a threshold value, and issuing a warning as soon as a desired value has been reached, fallen below or exceeded.