Abstract: Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Abstract: Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Abstract: Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Abstract: Computer-implemented method and system for modelling performance of a fixed-wing aerial vehicle (AV) with six degrees of freedom. The system comprises a collecting unit (330) to collect data from a plurality of modelling measures and modelling maneuvers; a processing unit (340) to communicate with a collecting unit (330). The processing unit (340) further sequentially processes data sets from a plurality of modelling measures and to determine models to generate an accurate APM. Modelling measures and modelling maneuvers are designed to modify an influence on the of variables of a model of the AV (100).

Abstract: A method for calculating an optimum maximum range cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including weight of the aircraft, an aircraft bearing and an atmospheric pressure, an atmospheric temperature, a wind speed and a wind bearing at the altitude of the aircraft; calculating a weight coefficient of the aircraft, a wind Mach number and an absolute value of a difference between the wind bearing and the aircraft bearing. Additionally, the method includes calculating an optimum Mach number of the aircraft, which provides the optimum maximum range cruise speed. The calculation of the optimum Mach number includes the weight coefficient, the wind Mach number, and the absolute value of the difference between the wind bearing and the aircraft bearing.

Abstract: Method for calculating an optimum economy cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including a weight of the aircraft, an aircraft bearing and an atmospheric pressure and temperature, a wind speed and a wind bearing at the altitude of the aircraft; calculating a cost index associated with the flight of the aircraft; calculating a weight coefficient of the aircraft, a cost index coefficient, a wind Mach number and an absolute value of a difference between the wind bearing and the aircraft bearing. Additionally, the method includes calculating an optimum Mach number of the aircraft, which provides the optimum economy cruise speed. The calculation of the optimum Mach number includes the weight coefficient, the cost index coefficient, the wind Mach number and the absolute value of the difference between the wind bearing and aircraft bearing.

Abstract: Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Abstract: The present disclosure relates to a method of inferring data relating to atmospheric conditions within an airspace of interest using observations of aircraft trajectories. Information relating to aircraft intent may also be inferred. Aircraft flying within the airspace are identified, and their trajectories and aircraft type are determined. Aircraft performance data relating to that type of aircraft is retrieved from memory, along with any filed aircraft intent data. Then, the atmospheric conditions data and, optionally, any missing aircraft intent data that, in combination with the filed aircraft intent data and the aircraft performance data, would give rise to the determined trajectory for each processed aircraft are inferred. The atmospheric data and optionally the missing aircraft intent data are provided as an output.

Abstract: A method for calculating an optimum maximum range cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including weight of the aircraft, an aircraft bearing and an atmospheric pressure, an atmospheric temperature, a wind speed and a wind bearing at the altitude of the aircraft; calculating a weight coefficient of the aircraft, a wind Mach number and an absolute value of a difference between the wind bearing and the aircraft bearing. Additionally, the method includes calculating an optimum Mach number of the aircraft, which provides the optimum maximum range cruise speed. The calculation of the optimum Mach number includes the weight coefficient, the wind Mach number, and the absolute value of the difference between the wind bearing and the aircraft bearing.

Abstract: Method for calculating an optimum economy cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including a weight of the aircraft, an aircraft bearing and an atmospheric pressure and temperature, a wind speed and a wind bearing at the altitude of the aircraft; calculating a cost index associated with the flight of the aircraft; calculating a weight coefficient of the aircraft, a cost index coefficient, a wind Mach number and an absolute value of a difference between the wind bearing and the aircraft bearing. Additionally, the method includes calculating an optimum Mach number of the aircraft, which provides the optimum economy cruise speed. The calculation of the optimum Mach number includes the weight coefficient, the cost index coefficient, the wind Mach number and the absolute value of the difference between the wind bearing and aircraft bearing.

Abstract: The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language.

Abstract: The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language.

Abstract: The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language.

Abstract: The present disclosure relates to a method of inferring data relating to atmospheric conditions within an airspace of interest using observations of aircraft trajectories. Information relating to aircraft intent may also be inferred. Aircraft flying within the airspace are identified, and their trajectories and aircraft type are determined. Aircraft performance data relating to that type of aircraft is retrieved from memory, along with any filed aircraft intent data. Then, the atmospheric conditions data and, optionally, any missing aircraft intent data that, in combination with the filed aircraft intent data and the aircraft performance data, would give rise to the determined trajectory for each processed aircraft are inferred. The atmospheric data and optionally the missing aircraft intent data are provided as an output.