Systems and methods for redundant braking and/or of remotely piloted vehicles are described. A redundant braking system includes a first onboard computing unit configured to receive sync data regularly from a main computing unit, receive heartbeat signal through a communication network from a remote pilot control unit, determine network failure if the heartbeat signal is not received for more than a threshold period of time, and generate a braking command. The system includes arrangements to activate brakes of the vehicle based on the braking command received from the local computing unit. The system may also generate a steering command to change the lane of the vehicle and park at a safe spot.

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.

In one example embodiment, a computer-implemented method includes receiving data representing a motion plan of the autonomous vehicle via a plurality of control lanes configured to implement the motion plan to control a motion of the autonomous vehicle, the plurality of control lanes including at least a first control lane and a second control lane, and controlling the first control lane to implement the motion plan. The method includes detecting one or more faults associated with implementation of the motion plan by the first control lane or the second control lane, or in generation of the motion plan, and in response to one or more faults, controlling the first control lane or the second control lane to adjust the motion of the autonomous vehicle based at least in part on one or more fault reaction parameters associated with the one or more faults.

Embodiments of the present application provide a method, device, storage medium, and electronic device for controlling flight equipment, wherein the method includes: acquiring positioning position information from a positioning system deployed on a target flight equipment; detecting an operating state of the positioning system according to positioning position information, wherein the operating state comprises: normal state and abnormal state; when the operating state is an abnormal state, controlling the target flight equipment to return to a ground control terminal according to the relative position information between the target flight equipment and the ground control terminal of the target flight equipment.

In one example embodiment, a computer-implemented method includes receiving data representing a motion plan of the autonomous vehicle via a plurality of control lanes configured to implement the motion plan to control a motion of the autonomous vehicle, the plurality of control lanes including at least a first control lane and a second control lane, and controlling the first control lane to implement the motion plan. The method includes detecting one or more faults associated with implementation of the motion plan by the first control lane or the second control lane, or in generation of the motion plan, and in response to one or more faults, controlling the first control lane or the second control lane to adjust the motion of the autonomous vehicle based at least in part on one or more fault reaction parameters associated with the one or more faults.

Described are devices, systems and methods for real-time remote control of vehicles with high redundancy. In some embodiments, two copies of at least one control command are received using two different wireless communication protocols, and are compared. The at least one control command is executed when the two copies are in agreement, but is rejected when the two copies differ. In other embodiments, additional wireless communication protocols may exist to provide a redundant mode of communication when one of the two different wireless communication protocols are unavailable. In yet other embodiments, redundant GPS units may be used to determine availability of any of the communication protocols, and relevant control commands may be downloaded in advance to circumvent a lack of coverage.

An inceptor apparatus for an aircraft comprises a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

In one example embodiment, a computer-implemented method includes receiving data representing a motion plan of the autonomous vehicle via a plurality of control lanes configured to implement the motion plan to control a motion of the autonomous vehicle, the plurality of control lanes including at least a first control lane and a second control lane, and controlling the first control lane to implement the motion plan. The method includes detecting one or more faults associated with implementation of the motion plan by the first control lane or the second control lane, or in generation of the motion plan, and in response to one or more faults, controlling the first control lane or the second control lane to adjust the motion of the autonomous vehicle based at least in part on one or more fault reaction parameters associated with the one or more faults.

A method for flight control of an aircraft with multiple actuators during flight is disclosed. For each actuator, a control command is computed according to at least one predetermined control law and based on pilot inputs and sensor measurements in relation to a physical state of the aircraft. The respective control commands are provided to the actuators. The control commands are independently monitored by estimating or measuring a current physical state of the aircraft and comparing it with the control commands. This comparison includes checking whether the control commands stabilize the aircraft in a stable state in the absence of both disturbances and pilot inputs according to at least one predefined criterion. If the monitoring indicates a lack of stability, transmission of the control commands is prevented and a backup control command is computed for each actuator.

A method for flight control of an aircraft with multiple actuators during flight is disclosed. For each actuator, a control command is computed according to at least one predetermined control law and based on pilot inputs and sensor measurements in relation to a physical state of the aircraft. The respective control commands are provided to the actuators. The control commands are independently monitored by estimating or measuring a current physical state of the aircraft and comparing it with the control commands. This comparison includes checking whether the control commands stabilize the aircraft in a stable state in the absence of both disturbances and pilot inputs according to at least one predefined criterion. If the monitoring indicates a lack of stability, transmission of the control commands is prevented and a backup control command is computed for each actuator.