A process and machine configured to predict and preempt an aerodynamic disturbance. The machine may include a BDE (Bhan-Donahue-Endres) adaptor configured to that comprises a specially programmed processor that has an adaptive learning control and rules to: modify a control augmentation system on an aerospace vehicle, to preclude an undesired state of the aerospace vehicle unaccounted for by control laws in current control augmentation systems; form a prediction for an airspeed of the aerospace vehicle that replaces an airspeed input from a sensor of the aerospace vehicle, in a phase of operation prone to instrumentation error, into the control augmentation system; generate an estimate, based upon the prediction, of an anticipated disturbance to a desired state of the aerospace vehicle; and generate, based upon the estimate, a command to a control element of the aerospace vehicle that preempts the undesired state of the aerospace vehicle.

Using a set of airflow sensors disposed on an airfoil of an aircraft, first airflow data including an amount of airflow experienced at each airflow sensor at a first time is measured. Using a trained neural network model, the first airflow data is analyzed to determine an airflow state of the aircraft. In response to determining that the aircraft is in the abnormal airflow state, a control surface and a power unit of the aircraft are adjusted. Responsive to the adjusting, the aircraft is returned to the normal airflow state.

A method executable by a first device for instructing a second device to adjust attitude includes determining a first directional vector of the second device relative to the first device. The method also includes transmitting an attitude adjustment instruction to the second device. The attitude adjustment instruction includes directional data indicating the first directional vector or directional data derived based on the first directional vector. The attitude adjustment instruction is configured to instruct the second device to adjust the attitude based on the directional data indicating the first directional vector or the directional data derived based on the first directional vector.

A method and system for determining in real time a vertical trajectory of an aircraft is provided. The method includes a step for providing an initial vertical trajectory comprising an initial phase for changing flight level according to a first slope, between a first point at a first altitude, and a second point at a second altitude, at least one step for modifying the vertical trajectory, comprising a phase for detecting a triggering element when the aircraft is at the first altitude, when said triggering element is detected, and a phase for determining a modified vertical trajectory, said modified vertical trajectory comprising a modified phase for changing flight level according to a second predefined slope, from a modified point at said first altitude, distinct from said first point, to said second altitude.

A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust, a flight computer and controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor. The controllable surfaces are controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction.

A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust, a flight computer and controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor. The controllable surfaces are controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction.