A robot system includes a mobile robot provided with a driving wheel and a driving motor, a load cell provided in the mobile robot, a spring connected to the load cell, an auxiliary wheel connected to the spring, and a controller configured to change a speed of the driving motor according to a sensing value of the load cell.

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.

A takeoff and landing device, includes: a fixing devices or a communication unit configured to be able to switch between a first state that is a state of preventing the unmanned aerial vehicle from taking off from the takeoff and landing device and a second state that is a state of not preventing taking off; a weight acquisition unit configured to acquire weight of the article that the unmanned aerial vehicle delivers; and a takeoff controller or a takeoff controller configured to switch a state of the fixing devices or the communication unit to the first state or the second state on the basis of the weight of the article acquired by the weight acquisition unit and of a reference value for determining whether it is an overload.

A method and system to control a rotor system includes automatically changing a rotor speed of the rotor system of the tiltrotor aircraft while moving the rotor system from a first position and a first rotor speed to a second position and a second rotor speed over a time period in accordance with an acceleration-rate profile that varies over the time period using a controller communicably coupled to the rotor system of the tiltrotor aircraft.

Methods and apparatus for automatically extending aircraft wing flaps in response to detecting an excess energy steep descent condition are described. An example control system of an aircraft includes one or more processors. The one or more processors determine whether the aircraft is experiencing an excess energy steep descent (EESD) condition. In response to determining that the aircraft is experiencing the EESD condition, the one or more processors command an actuator of the aircraft coupled to a flap of the aircraft to extend the flap from a current flap position to a subsequent flap position defined by a flap extension sequence.

A system for path control for a mobile unmanned vehicle in an environment is provided. The system includes: a sensor connected to the mobile unmanned vehicle; the mobile unmanned vehicle configured to initiate a first fail-safe routine responsive to detection of an object in a first sensor region adjacent to the sensor; and a processor connected to the mobile unmanned vehicle. The processor is configured to: generate a current path based on a map of the environment; based on the current path, issue velocity commands to cause the mobile unmanned vehicle to execute the current path; responsive to detection of an obstacle in a second sensor region, initiate a second fail-safe routine in the mobile unmanned vehicle to avoid entry of the obstacle into the first sensor region and initiation of the first fail-safe routine.

An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.

Disclosed is an autopilot system for a helicopter, the helicopter having: a cyclic and a collective that are physically coupled to helicopter actuators that control cyclic and collective pitch of main rotor blades of the helicopter and anti-torque pedals that are physically coupled to helicopter actuators that control the pitch of tail rotor blades of the helicopter; and at least one servomechanism configured to amplify force applied by the pilot to the cyclic, collective and/or anti-torque pedals; wherein the autopilot system comprises an autopilot actuator configured to: in an autopilot mode, control direction or orientation of the helicopter by applying force to a control link that is physically coupled to one of the helicopter actuators; and in a manual mode, provide stability or control augmentation by applying a force on one of the cyclic, the collective or one or both of the anti-torque pedals to influence the pilot's inputs to urge the helicopter away from a particular flight condition dependent on monitored aircraft parameters.

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.

A method for controlling movement of a robot includes inputting a first linear velocity parameter and a first angular velocity parameter, which are specified as the robot moves, into a first limit model for limiting a centripetal acceleration to correct the first linear velocity parameter and the first angular velocity parameter, thereby calculating a second linear velocity parameter and a second angular velocity parameter, inputting the second linear velocity parameter and the second angular velocity parameter into at least one of a second limit model for limiting a linear velocity and a third limit model for limiting an angular velocity to correct the second linear velocity parameter and the second angular velocity parameter, thereby calculating a third linear velocity parameter and a third angular velocity parameter, and controlling the movement of the robot based on the third linear velocity parameter and the third angular velocity parameter.