A process and machine configured to predict and preempt an undesired load and/or bending moment on a part of a vehicle resulting from an exogenous or a control input. The machine may include a predictor with an algorithm for converting parameters from a state sensed upwind from the part into an estimated normal load on the part and a prediction, for a future time, of a normal load scaled for a weight of the aerospace vehicle. The machine may: produce, using a state upwind from the part on the aerospace vehicle and/or a maneuver input, a predicted state, load and bending moment on the part at a time in the future; derive a command preempting the part from experiencing the predicted load and bending moment; and actuate the command just prior to the part experiencing the predicted state, thereby alleviating the part from experiencing the predicted load and bending moment.

Systems and aircraft are provided. An avionics system includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: determine a first measured value of a flight characteristic of the aircraft at a first position of the aircraft; execute at least one flight maneuver between the first position and a second position of the aircraft; generate a predicted energy change between the first position and the second position based on the at least one flight maneuver and an energy state model; determine a second measured value of the flight characteristic of the aircraft at the second position; and generate an adjustment to the energy state model based on the first measured value, the second measured value, and the predicted energy change.

A technique for controlling an unmanned aerial vehicle (UAV) includes monitoring a sensed airspeed of the UAV, obtaining a commanded speed for the UAV, wherein the commanded speed representing a command to fly the UAV at a given speed relative to an airmass or to Earth, and when the commanded speed is greater than the sensed airspeed, using the commanded speed in lieu of the sensed airspeed to inform flight control decisions of the UAV.

A method including propelling a vehicle disposed in a medium. The vehicle includes a body, a propulsion mechanism connected to the body, and a direction control system. The vehicle is subject to advection caused by movement of the medium. The method also includes commanding the vehicle to perform a navigation course comprising a closed course-over-ground. The method also includes periodically adjusting navigation of the vehicle along the closed course-over-ground such that a course-through-the-medium turn-rate is varied in a manner that causes a course-over-ground turn-rate of the vehicle to be held constant, thereby minimizing the impact of medium advection on vehicle speed over ground.

A heading control system for an aircraft arranged to maintain a heading of an aircraft by controlling a nose wheel angle of the aircraft. The heading control system includes an interface arranged to receive a bias signal indicating a bias towards the port or the starboard of the aircraft and one or more processors. The one or more processors are arranged to determine, based on the bias signal, an offset angle defining an offset from a longitudinal axis of the aircraft and to perform a control process to control the nose wheel angle within an angular range based on the offset angle.

Systems and aircraft are provided. An avionics system includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: determine a first measured value of a flight characteristic of the aircraft at a first position of the aircraft; execute at least one flight maneuver between the first position and a second position of the aircraft; generate a predicted energy change between the first position and the second position based on the at least one flight maneuver and an energy state model; determine a second measured value of the flight characteristic of the aircraft at the second position; and generate an adjustment to the energy state model based on the first measured value, the second measured value, and the predicted energy change.

A process and machine configured to predict and preempt an undesired load and/or bending moment on a part of a vehicle resulting from an exogenous or a control input. The machine may include a predictor with an algorithm for converting parameters from a state sensed upwind from the part into an estimated normal load on the part and a prediction, for a future time, of a normal load scaled for a weight of the aerospace vehicle. The machine may: produce, using a state upwind from the part on the aerospace vehicle and/or a maneuver input, a predicted state, load and bending moment on the part at a time in the future; derive a command preempting the part from experiencing the predicted load and bending moment; and actuate the command just prior to the part experiencing the predicted state, thereby alleviating the part from experiencing the predicted load and bending moment.

Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Embodiments of the present disclosure provide improved user interface(s) that intuitively convey information via a dynamic wind indicator. Embodiments include a dynamic wind indicator that is specially configured to visually indicate data value(s) via one or more visual properties of the dynamic wind indicator. As updated data is received, the dynamic wind indicator is updated in real-time to visually indicate the most up-to-date data value(s), for example to intuitively visually indicate effects of wind on an aerial vehicle. Some example embodiments receive wind movement data including wind speed data and wind directionality data. Some such example embodiments cause rendering of a user interface including a dynamic wind indicator that [1] visually indicates a direction of a 3D environment based on the wind directionality data, and [2] has at least one visual property configured based on the wind speed data.

A vehicle may include a sensor and a proactive vehicle controller that is capable of proactively altering one or more vehicle operating parameters in response to detecting a force caused by an environmental event that will be exerted on a chassis of the vehicle. The sensor has a field-of-view that includes the direction of travel of the vehicle. The sensor may detect objects in the field-of-view and, based at least in part on the behavior of the objects in the field-of-view, predicts the force exerted on the object by an environmental event. Based on the predicted force, the proactive vehicle controller proactively adjusts one or more vehicle operating parameters to minimize the effect of the force that will be exerted on the vehicle by the environmental event.