A method for providing adaptive control to a fly-by-wire aircraft includes measuring via at least one first sensor a characteristic of at least one component of the aircraft and measuring via at least one second sensor a state of the aircraft. Using the characteristic of at least one component and the state of the aircraft, a determination of at least one of an actual damage and remaining life of the at least one component is made. The operational envelope of the aircraft is adapted based on the at least one of actual damage and remaining life of the at least one component. Adapting the operational envelope includes adjusting an outer boundary thereof to prohibit operation exceeding a safe operation threshold and generating an intermediate boundary of the operational envelope. Operation of the aircraft within the intermediate boundaries minimizes further damage accrual of the at least one component.

Methods and systems according to one or more examples are provided for avoiding foreign object strikes on rotorcraft vehicles. In one example, a vehicle comprises a rotor comprising a rotor blade, a first sensor configured to provide first sensor information associated with an object proximate the vehicle, and a second sensor configured to provide second sensor information associated with the rotor. The vehicle further comprises a processor coupled to the first sensor and the second sensor configured to selectively control the rotor to minimize damage to the vehicle by the object based on the first and second sensor information.

Performance anomalies in complex systems can be difficult to identify and diagnose. In an example, CPU-usage associated with one or more of the systems can be determined. An anomalous event can be determined based on the determined CPU-usage. In some examples, based at least in part on determining the event, the system may be controlled in a safe state and/or reconfigured to obviate the anomalous event.

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.

A vehicle control apparatus includes one or more electronic control units configured to execute autonomous traveling control of a vehicle based on detection results of a plurality of sensors, a cleaner configured to clean dirt off of at least one of the plurality of sensors. The one or more electronic control units are configured to determine, when cleaning of dirt of a first sensor is executed, whether or not execution of the autonomous traveling control can be continued based on a detection result of one or more remaining sensors among the plurality of sensors, control the vehicle such that a required detection range is narrowed in case it is determined that the execution of the autonomous traveling control cannot be continued, and control the cleaner such that the cleaner cleans dirt off of the first sensor while continuing the execution of the autonomous traveling control.

The invention relates to an automated method for influencing a gust load of an aircraft (6), wherein the torque (MI) at least of an electromotive thrust generating unit (1) arranged on a wing (4) of the aircraft (6) is modified such that the root bending torque (M2) of the wing (4) generated by the gust load is reduced. The invention also relates to an associated apparatus and an aircraft and a computer program product and a computer-readable medium for carrying out the method.

Physical and logical components of a long line loiter control system address control of a long line loiter maneuver conducted beneath a carrier, such as a fixed-wing aircraft. Control may comprise identifying, predicting, and reacting to estimated states and predicted states of the carrier, a suspended load control system, and a long line. Identifying, predicting, and reacting to estimated states and predicted states may comprise determining characteristics of state conditions over time as well as response time between state conditions. Reacting may comprise controlling a hoist of the carrier, controlling thrusters of the suspended load control system, and or controlling or issuing flight control instructions to the carrier so as not to increase the response time and or to avoid a hazard.

Device and method for reducing gust loads acting on control surfaces of an aircraft. Each control surface is movable by at least one actuator, and a flight control system provides reference variables X.sub.soll and {dot over (X)}.sub.soll to actuate the actuator of each control surface. X.sub.soll indicates a target position, force, or moment of the actuator, and {dot over (X)}.sub.soll indicates a time derivative of X.sub.soll. The device includes: a first sensor system identifying a position, force, or moment, indicated by variable F.sub.ext,Boe, as produced by gusts acting from outside on the control surface; and a regulator regulating the actuator of the control surface based on F.sub.ext,Boe, X.sub.soll and {dot over (X)}.sub.soll, and X.sub.A and {dot over (X)}.sub.A, resulting from the actuator acting on the control surface and detected by a second sensor system, wherein regulation of the actuator by the regulator enables compensation of the position, force, or moment produced by gusts acting on the control surface.

An operating system for an automated vehicle includes a failure-detector and a controller. The failure-detector detects a component-failure on a host-vehicle. Examples of the component-failure include a flat-tire and engine trouble that reduces engine-power. The controller operates the host-vehicle based on a dynamic-model. The dynamic-model is varied based on the component-failure detected by the failure-detector.

Aspects of the disclosure relate to stopping a vehicle. For instance, a vehicle is controlled in an autonomous driving mode by generating first commands for acceleration control and sending the first commands to an acceleration and/or steering actuator of an acceleration system of the vehicle in order to cause the vehicle to accelerate. Acceleration and/or orientation of the vehicle is monitored while the vehicle is being operated in an autonomous driving mode. The monitored acceleration and/or orientation is compared with the first commands. An error with the acceleration and/or steering system is determined based on the comparison. When the error is determined, the vehicle is controlled in the autonomous driving mode by generating second commands which do not require any acceleration and/or steering.