A system includes a signal monitor to monitor a time rate of change of a revolutions per minute (RPM) trim signal that is received from an RPM command path to control a velocity of a helicopter rotor. An icing detector detects for the presence of ice accumulation on the helicopter rotor by comparing the time rate of change of the RPM trim signal to a predetermined threshold for the time rate of change.

According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface.

A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

Technology for achieving the behavior and benefits of traditional cyclic control in one rotor may be implemented with a simple under-actuated passive mechanism. An air vehicle employing the disclosed technology maintains lifting thrust by regulating the average rotor speed and generates control moments through coordinated pulsing of the motor torque. Rapid pulsing of the motor torque induces oscillations in propeller angle of attack, and so causes cyclic control without requiring the traditional auxiliary actuators and linkages. The MAV propulsion system is capable of using a minimum number of actuators in dual roles of thrust and moment objectives.

A system including an aerial vehicle having an airframe and a power source onboard the aerial vehicle, wherein the aerial vehicle includes a landing gear structure having a first electrical contact and a second electrical contact, and a charging station having a first electrical contact and a second electrical contact, wherein the aerial vehicle is programmed to dock with the charging station when the power source is in need of recharging, the docking being a mechanical engagement between the first electrical contact and the second electrical contact of the aerial vehicle with the first electrical contact and the second electrical contact of the charging station is provided. A method for continuous surveillance utilizing the aerial vehicles and charging stations is also provided.

A system for monitoring movements of rotor blades attached by flapping hinges to a central head or hub of a helicopter. At least one sensor is arranged to continuously measure vertical angular movement of a rotor blade and/or the flapping hinge. Also a method for monitoring movements of rotor blades attached by flapping hinges to a central head or hub of a helicopter.

A system and method for preventing a flame out condition in at least one engine, includes detecting a moisture content exceeding a threshold moisture content in an operating environment of the at least one engine, and engaging at least one igniter associated with the at least one engine in response to the moisture content.

According to an aspect, a method of performing context-aware landing zone classification for an aircraft includes accessing a landing zone map, by a context-aware landing zone classification system of the aircraft, to identify potential landing zones. A database on the aircraft includes land cover map data and impervious surface map data. The database is queried to extract context data. The context data include land cover characteristics and impervious surface characteristics associated with locations corresponding to the landing zone map. The context-aware landing zone classification system of the aircraft evaluates the potential landing zones in view of the context data to adjust classifications of the potential landing zones and produce a context-aware landing zone classification of the potential landing zones. The context-aware landing zone classification of the potential landing zones is provided to landing zone selection logic of the aircraft to select a final landing zone.

A battery powered remotely controlled robot is equipped with a drive subsystem for ground travel, a flight subsystem for flight operations, and an obstacle detection subsystem. The robot is configured so that during a mission the drive subsystem is energized to maneuver the robot on the ground for a majority of the mission. The robot is further configured so that upon detection of an obstacle, the flight subsystem is energized to traverse the obstacle. The fight subsystem is energized only to traverse obstacles thus saving battery power and increasing the mission time.