Fault-tolerant lateral waypoint sequencing is provided for a system that includes at least a first flight management computer and a second flight management computer. A processing operation associated with lateral leg sequencing of an aircraft flight plan is implemented in the flight management…
The system has a pilot symbol generating unit (GS) provided in helmet display at virtual positions fixed relative to a terrestrial mark (RT) to compute representations comprising targets when a helicopter (H) rejoins or remains in vicinity of a preset position in the frame. One of the targets is…
The method involves allowing a pilot to enter setpoints such as speed setpoint and altitude setpoint, by a flight control interface unit (2). An interface unit (4) is envisaged for allowing the pilot to generate a geographical constraint represented by a distance ahead of an aircraft. A position…
The present invention provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A flight intent description is parsed to…
The instrument (10) has an inertial sensor (1) and a pressure sensor (2) connected to a calculation unit (3) that determines critical flight information for an aircraft. The calculation unit includes an output connected to actuators (15) of autopilot of the aircraft and an input connected to a full…
An improved Horizontal Situation Indicator module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from a GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading…
The system (1) has geodetic position determination arrangement (20) to determine external actual position of automotive, unmanned, remotely controllable air vehicle (10) such as aircraft. A control unit is configured such that vehicle is positioned continuously in defined target position (6)…
The method involves measuring current values (N1c1-N1c4) of driving parameters associated to external engines (M1, M4) and internal engines (M2, M3). Detection is made whether difference between the current values of the driving parameters associated with each engine and a determined intermediate…
The present invention provides a method of operating an aircraft whereby actual acceleration of an aircraft is used as the direct measure of the capability of the aircraft to takeoff. Thus, a minimum takeoff acceleration is determined for an aircraft and then through appropriate sensing means for…