A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

A vehicle includes a vehicle platform, an antenna, and an antenna positioner configured to position the antenna relative to the vehicle platform. An inertial navigation system (INS) is associated with the vehicle platform and configured to generate INS output data. An inertial measurement unit (IMU) is associated with the antenna positioner and configured to generate IMU output data having a timing latency difference relative to the INS output data. A controller may be configured to control the antenna positioner based upon the INS output data and the IMU output data adjusted for the timing latency therebetween.

A system for electric aircraft navigation includes a sensor configured to detect a navigation signal, a flight controller, wherein the flight controller is configured to receive the navigation signal, identify a navigation status as a function of the navigation signal, and determine an aircraft adjustment as a function of the navigation status, and a pilot display, wherein the pilot display is configured to display the aircraft adjustment to a user, and present an autonomous function configured to enact the aircraft adjustment automatically.

A method of restoring navigational performance for a navigational system, the method comprising receiving by a first navigational system and a second navigational system a collection of data points to establish a real-time navigational route for the aircraft, comparing navigational performance values and/or drift ranges and establishing a new navigational route based on the collection of data points.

Flight control information systems, flight guidance display, and aircraft are provided. A navigational information system includes an input configured to receive a flight plan wherein the flight plan includes a first waypoint, a second waypoint, a third waypoint, and future waypoints, a user interface operative to generate a control signal in response to a user input, a display configured to display a graphical user interface, a processor operative to receive the flight plan from the input, to generate the graphical user interface to include to the first waypoint and the second waypoint and to couple the graphical user interface to the display, the processor being further operative to generate the graphical user interface in to include the first waypoint and the third waypoint in response to the control signal and to couple the graphical user interface to the display.

A system may include a user interface and a processor. The processor may be configured to (a) pre-arm multiple actions according to a conditional timeline and any associated trigger events, and (b) output commands to cause the multiple actions to be completed at times consistent with the conditional timeline and any associated trigger events.

Methods and systems are provided for guiding or otherwise assisting energy management of an aircraft radar vectoring en route to a runway. A method involves determining a predicted lateral trajectory for the radar vectoring in accordance with interception criteria, wherein the lateral trajectory comprises a sequence of segments for satisfying the interception criteria from a current location of the aircraft and each navigational segment of the sequence is associated with an anticipated aircraft heading assignment. The method determines a reference vertical trajectory corresponding to the lateral trajectory, determines a target value for an energy state parameter of the aircraft at the current location on the lateral trajectory using the reference vertical trajectory, and provides indication of a recommended action to reduce a difference between a current value for the energy state parameter and the target value.

An advisory module may include processing circuitry configured to receive data indicative of internal factors and external factors related to route optimization of a combined route of a subject. The combined route may include an air segment and a ground segment, and at least some of the external factors may include dynamic parameters that are changeable while the air segment or ground segment is being transited by the subject to a ground objective. The processing circuitry may be further configured to generate a guidance option to deliver the subject to the ground objective based on integration of the internal factors and the external factors to optimize a route to the ground objective, and provide a graphical representation of the guidance option along with comparative data or context information associated with the route.

A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.