A system for flight control system using simulator data for an electric aircraft is presented. The system includes a computing device, the computing device configured to receive a plurality of measured flight data, simulate a plurality of aircraft performance model outputs as a function of a flight simulator and the plurality of measured flight data, determine a moment datum as a function of the plurality of measured flight data and the plurality of aircraft performance model outputs, generate an allocation command datum as a function of the moment datum and the plurality of aircraft performance model outputs, and perform a torque allocation on a flight component of a plurality of flight components as a function of the allocation command and the moment datum.

Methods and systems for providing vertical flight guidance for an aircraft. Vertical flight guidance for the aircraft is provided by an aircraft computer in an altitude capture mode for commanding the aircraft to capture a target altitude. At least one engine inoperative condition is detected by the computer, while in the altitude capture mode. In response to detecting the at least one engine inoperative condition, the computer causes an automatic transition (e.g., no pilot action on a flight level change (FLC) pushbutton on a flight control panel) of the vertical flight guidance for the aircraft from the altitude capture mode to an already existing mode that is flight level change with modified control parameters and provides vertical flight guidance in the flight level change mode for commanding the aircraft to capture the target altitude while maintaining airspeed of the aircraft substantially at a target airspeed.

The present disclosure relates generally to control systems, and in particular apparatus, methods, and systems for controlling flights remotely or onboard the vehicle. More specifically, the present disclosure describes embodiments of a control system that allows a user to control the motion of a control target in or along one or more degrees of freedom using a single controller.

Systems and methods for lag optimization of pilot intervention is provided. A critical event may be identified while an electric aircraft is in an autopilot mode and operating primarily under autonomous functions; as a result, a flight controller of the system may switch from an autopilot mode to a manual mode, allowing pilot intervention. System made determine a lag duration as a function of the critical event and a phase of operation of the electric aircraft to determine a lag duration before pilot intervention occurs.

A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.

An air vehicle includes a flight computer, a fuselage, and two rotors mounted symmetrically with respect to the fuselage. Each of the two rotors includes a servo mechanism to tilt a respective rotor of the two rotors about two axes of the respective rotor. The flight computer is configured to send control parameters to each of the two rotors, the control parameters including a rotational speed, a first tilt angle about a first axis of the two axes of the respective rotor, and a second tilt angle about a second axis of the two axes of the respective rotor. A method for operating the air vehicle is also provided.

Various reconfigurations of propellers, propeller blades, and/or blade sections of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, propellers, propeller blades, and/or blade sections of the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, angular orientations, positions, and/or lengths of one or more propellers, propeller blades, and/or blade sections of propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

A loss-of-control prevention and recovery automatic control system of an aircraft is provided having a plurality of flight control mode, including a nominal flight control mode, a loss-of-control prevention control mode, a loss-of-control arrest control mode, and a nominal flight restoration control mode, as well as a supervisory control system capable of monitoring the flight states and flight events of the aircraft and determining which flight control mode to activate.