A system for controlling a pitch of an endless track vehicle for driving the endless track vehicle in a given direction; monitoring a pitch angle of the endless track vehicle while moving along the given direction; and upon determining that the pitch angle is varying, controlling the driving of the endless track vehicle to control a rate of variation of the pitch angle of the endless track vehicle. The endless track vehicle may include a body defining a load bearing surface. Track(s) is rotatably mounted to the body to move the body. A motorization unit actuates the track(s). A drive system operates the motorization unit.

Systems and vehicle are provided. A vehicle system for a vehicle includes: a trajectory selection module configured to select a potential vehicle path relative to a current vehicle movement condition; a trajectory movement condition module configured to estimate a modeled movement condition of the vehicle along the potential vehicle path; a limit comparison module configured to determine whether the modeled movement condition violates vehicle limits; and a violation indicator module configured to generate an indication of impending violation.

Described herein are technologies relating to computing a likelihood of an operation-influencing event with respect to an autonomous vehicle at a geographic location. The likelihood of the operation-influencing event is computed based upon a prediction of a value that indicates whether, through a causal process, the operation-influencing event is expected to occur. The causal process is identified by means of a model, which relates spatiotemporal factors and the operation-influencing events.

A stabilized a hydrofoil water craft comprising: a water-craft base member, a hydrofoil mast having proximal and distal portions; said proximal portion mechanically connected to said bottom side of said water-craft base member, a fuselage mechanically connected to said distal portion of said at least one hydrofoil mast, a rudder configured for controlling a yaw angle of said water craft, an elevator rotatable around an axis lying in a plane parallel to water-craft base member and a stabilization arrangement further comprising at least one sensor configured for detecting a 3D orientation of said water-craft base member, an estimator configured for estimating the 3D orientation, actuators for manipulating the rudder and elevator and a controller for analyzing the estimated 3D orientation and controlling the actuators. In response to a disturb roll inclination of the water craft, the controller generates a command to a rudder actuator to compensate the detected inclination.

A system for preconditioning a power source of an electric aircraft is presented. The apparatus includes a power source of an electric aircraft, a computing device, and a user device. The computing device is configured to receive a flight plan, determine a predicted power usage model as a function of the flight plan, and initiate a power source modification on the electric aircraft as a function of the predicted power usage model. The user device is configured to display a flight performance infographic as a function of the predicted power usage model.

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.

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.

A method of controlling rotor moments includes receiving, in a flight control computer (FCC) a rotor moment reference value based on pilot inceptor inputs, sensing rotor moment from one or more sensors, receiving, in the FCC, a rotary wing aircraft condition parameter, and establishing, through the FCC, a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.