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.

An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.

A system for taking into account micro wind conditions in a region. The system comprises a plurality of aerial vehicles within the region and a wind speed calculator. Each of the plurality of aerial vehicles has an altitude sensor and a GPS receiver. The wind speed calculator is configured to determine wind vectors within the region using measurements from the plurality of aerial vehicles.

An aerial vehicle control system includes an aerial vehicle and a computing device. The aerial vehicle includes an altitude controller and a lateral propulsion controller. The computing device includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the computing device to obtain location data corresponding to a location of the aerial vehicle; obtain wind data; determine an altitude command, a latitude command, and a longitude command based on at least one of the location data or the wind data; cause the altitude controller to implement at least one of the altitude command, the latitude command, or the longitude command; and cause the lateral propulsion controller to implement at least one of the altitude command, the latitude command, or the longitude command.

Systems, aircraft, and non-transitory media are provided. An avionics system for an aircraft 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: generate a lateral component and a longitudinal component of a measured moving air mass relative to the aircraft; generate a plurality of wind independent positions of the aircraft along a potential aircraft trajectory based on a prediction model; and generate a plurality of wind corrected positions of the aircraft based on the plurality of wind independent positions, on the lateral component, and on the longitudinal component.

An apparatus for guiding an aircraft includes: an air velocity sensor disposed on the aircraft and configured to sense a speed and direction of a wind remote to the aircraft to provide remote wind speed and direction data; a flight control actuator coupled to a flight control device; and a flight controller communicably coupled to the air velocity sensor, the flight controller having an input section that receives the remote wind speed and direction data from the air velocity sensor, a processor configured to determine a magnitude and direction of the wind with respect to a planned flight route and to predict an influence acting on the aircraft due to the magnitude and direction of the wind with respect to the planned flight route, and an output section communicably coupled to the flight control actuator to provide a control signal that results in the aircraft counteracting the predicted influence.

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.

An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.

Systems, methods, aircraft, non-transitory media, and memories are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for converting between airspeed types and the one or more data processors is configured to execute the instructions to: generate a calibrated airspeed of the aircraft; convert the calibrated airspeed to an actual true airspeed of the aircraft; determine an initial approximate relationship between the calibrated airspeed and a computed true airspeed as a function of a pressure altitude of the aircraft; generate an adjusted approximate relationship based on the actual true airspeed and the initial approximate relationship at a chosen pressure altitude; and estimate a future airspeed of the aircraft based on the adjusted approximate relationship and a future altitude.

System and techniques for drone obstacle avoidance using real-time wind estimation are described herein. A wind metric is measures at a first drone and communicated to a second drone. In response to receiving the wind metric, a flight plan of the second drone is modified based on the wind metric.