Abstract: An interactive system for unlocking a locked airplane cockpit door having at least one ground station and at least one system for transmitting data between the ground station and airplane, including a ground station signal for actuating a door unlock mechanism. The airplane has: a passenger cabin located door unlock request unit to generate a door unlock request signal; a unit to transmit the request signal; at least one image capture unit in the passenger cabin or a cockpit and a unit to transmit images; a unit for receiving a door unlock signal; and an on-board computer, configured to receive the door unlock signal from the receiving unit and activate the door unlock mechanism. The ground station is connected to at least one receiving station for door unlock request and image signals transmitted from airplanes and is provided with or connected to a transmitting unit for door unlock signals.

Abstract: An interactive system for unlocking a locked airplane cockpit door having at least one ground station and at least one system for transmitting data between the ground station and airplane, including a ground station signal for actuating a door unlock mechanism. The airplane has: a passenger cabin located door unlock request unit to generate a door unlock request signal; a unit to transmit the request signal; at least one image capture unit in the passenger cabin or a cockpit and a unit to transmit images; a unit for receiving a door unlock signal; and an on-board computer, configured to receive the door unlock signal from the receiving unit and activate the door unlock mechanism. The ground station is connected to at least one receiving station for door unlock request and image signals transmitted from airplanes and is provided with or connected to a transmitting unit for door unlock signals.

Abstract: Method, computer program to implement method, storage medium to store the program and apparatus for computing Signal-in-Space Accuracy (SISA) parameters in a regional or Global Navigation Satellite System (GNSS). The method includes at least of: determining individual Signal-in-Space Error (SISE) vectors; mapping individual SISE vectors to a service area; accumulating empirical sample sets; processing density functions of estimations of accumulated sample sets; individually overbounding density functions in one of an overbounding sense related to the regional or GNSS or in a paired overbounding with excess mass sense; and selecting a worst case according to predefined requirements.

Abstract: A method for determining overbounds comprises the steps of determining conservative overbounds (qi) of at least one error (?i) in a first phase space, multiplying the conservative overbounds (qi) of errors (?i) in the first phase space by a first parameter (?(?x)·2) and a second parameter (?(x)·2), and determining an upper bound for the integrity risk at the alert limit (pw,int(AL)) in a second phase space using overbounds (qi) of errors (?i) in the first phase space by the first parameter (?(?x)·2) and the second parameter (?(x)·2).

Abstract: Method, computer program to implement method, storage medium to store the program and apparatus for computing Signal-in-Space Accuracy (SISA) parameters in a regional or Global Navigation Satellite System (GNSS). The method includes at least of: determining individual Signal-in-Space Error (SISE) vectors; mapping individual SISE vectors to a service area; accumulating empirical sample sets; processing density functions of estimations of accumulated sample sets; individually overbounding density functions in one of an overbounding sense related to the regional or GNSS or in a paired overbounding with excess mass sense; and selecting a worst case according to predefined requirements.

Abstract: A satellite navigation system generates a smooth and flexible parameterization of satellite orbits and/or clock corrections. The satellite orbit(s) and/or the satellite clock corrections, are described by a first function system of advancing differentiable functions having a high approximation quality and long range of influence. Satellite orbits and/or clock corrections parameterized from the first function system are transmitted from a central ground processing unit to satellite(s) and then to a user device. (Alternatively, transmission may be effected via only a ground infrastructure.) In addition, a second advancing function system of at least continuous functions of moderate approximation quality and a very short range of influence may be provided, which permits a conversion to the first function system, particularly via the user terminal. Thus, the time required to determine the first navigation information (the time to the first fix) can be significantly shortened.

Abstract: Operation of a satellite navigation system utilizes a method of generating a sufficiently smooth and very flexible parameterization of satellite orbits and/or satellite clock corrections of a satellite. For description of the satellite orbit(s) and/or of the satellite clock corrections, a first system of advancing differentiable functions (first function system) is provided which has a high approximation quality and a long range of influence. The satellite orbits and/or satellite clock corrections parameterized from the first function system are transmitted from a central ground processing unit to one or more satellites and then to a user device. (Alternatively, the transmission may take place without utilizing the space segment, via only a ground infrastructure.

Abstract: A method for determining overbounds comprises the steps of determining conservative overbounds (qi) of at least one error (?i) in a first phase space, multiplying the conservative overbounds (qi) of errors (?i) in the first phase space by a first parameter (?(?x)·2) and a second parameter (?(x)·2), and determining an upper bound for the integrity risk at the alert limit (pw,int(AL)) in a second phase space using overbounds (qi) of errors (?i) in the first phase space by the first parameter (?(?x)·2) and the second parameter (?(x)·2).