In an embodiment, a method of managing force equalization (FEQ) on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a measured force applied by a first actuation system in relation to a control surface, where the control surface is redundantly serviced by a plurality of actuation systems. The method also includes updating a measured-force time series for the first actuation system with the measured force. The method also includes analyzing movement over at least a portion of the measured-force time series. The method also includes identifying a force-fight cycle in the measured-force time series. The method also includes indicating the force-fight cycle in cumulative force-fight cycle data for the first actuation system.

A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.

A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

A device for detecting the approach of a vortex ring state for a rotary wing aerodyne, the detection device including a set of vibration sensors configured to be distributed in or on the aerodyne, and a data processing unit configured to receive in real time measurement data from the sensors, process the data in order to calculate in real time the vibration spectrum of the aerodyne, detect in real time, by vibration analysis, the approach of a vortex ring state as a function of the calculated vibration spectrum, and issue an alarm in the event of detection of the approach of a vortex ring state.

An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

A propeller guard 2 includes: a propeller guard body 10 configured to surround a propeller 30 of a flight vehicle 20; and a rod-shaped body 40 provided on an upper portion of the propeller guard body 10 and including a first end 44 and a second end 41, in which the first end 44 of the rod-shaped body 40 is provided near a peripheral portion of an upper surface of the propeller guard body 10, and the rod-shaped body 40 extends while passing above the upper surface of the propeller guard body 10 as viewed from vertically above.

A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

The present invention relates to a downwash blocking apparatus of air mobility configured such that multi-stage guide shells configured for blocking downwash and guiding the downwash to a discharge portion of a vertiport are mounted to a rotor guide of a flying vehicle for air urban mobility to be movable upwards and downwards, whereby it is possible to prevent the downwash from affecting passengers at the time of boarding and deboarding, and therefore it is possible to solve passenger inconvenience at the time of boarding and deboarding.

A method for controlling an unmanned aerial vehicle within a flight operating space. The unmanned aerial vehicle includes one or more sensor arrays on each spar. The method includes determining, using a plurality of sensor arrays, a flight path for the unmanned aerial vehicle. The method also includes receiving, by at least one sensor array of the plurality of sensor arrays, sensor data identifying at least one object in the operating space. The sensor data is transmitted over a communications bus connecting components of the UAV. The method further includes determining, by one or more processors onboard the unmanned aerial vehicle, a flight path around the at least one object. The method also includes generating, by the one or more onboard processors, a first signal to cause the unmanned aerial vehicle to navigate within the operating space around the at least one object.