Abstract: A method of determining structural health of an assembly includes determining a Margin of Safety (MSH) value for at least one of a plurality of components in the assembly when the assembly is healthy. The method includes determining if damage to the assembly has occurred. If damage to the assembly has occurred, the method includes determining a Margin of Safety (MSD) value for at least one of the plurality of components in the assembly when the assembly is damaged. The method includes determining a Structural Health Index (SHI) of the assembly based on the MSD value for the at least one undamaged component.

Abstract: A method of monitoring usage to determine accumulated component fatigue damage includes evaluating available data for calculating an accumulated component fatigue damage for a component over a pre-determined time frame. The method includes determining at least one available method for calculating the accumulated component fatigue damage based on the available data. The method includes determining the accumulated component fatigue damage for the component using the at least one available method.

Abstract: A method of assessing structural health includes receiving an anomaly detector, receiving an anomaly detection threshold, and receiving a strain measurement for a structure of interest. A rating is generated for the strain measurement using the anomaly detector and compared with the anomaly detection threshold. Health of the structure of interest is determined based on the comparison of the rating and the anomaly detection threshold.

Abstract: A method of monitoring usage to determine accumulated component fatigue damage includes evaluating available data for calculating an accumulated component fatigue damage for a component over a pre-determined time frame. The method includes determining at least one available method for calculating the accumulated component fatigue damage based on the available data. The method includes determining the accumulated component fatigue damage for the component using the at least one available method.

Abstract: Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

Abstract: According to one aspect, a controller, including a processor, sets an initial vibration frequency to be applied to an airframe. The controller commands one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency. The controller determines a vibration response of the airframe at the initial vibration frequency using sensors. The controller sweeps through a range of vibration frequencies to be applied to the airframe. The one or more force generators are commanded to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies. The controller determines a range of vibration responses of the airframe over the range of vibration frequencies using the sensors. A global stiffness of the airframe is determined based on the vibration response and the range of vibration responses. The controller reports results of the determined global stiffness of the airframe.

Abstract: Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

Abstract: Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

Abstract: Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

Abstract: A coaxial, dual rotor system for an aircraft includes a first rotor assembly located at a rotor axis and a second rotor assembly located at the rotor axis. An aerodynamic fairing is positioned between the first rotor assembly and the second rotor assembly along the rotor axis. A planetary gear arrangement is operably connected to the fairing and operably connected to an airframe of the aircraft to maintain a selected rotational orientation of the fairing about the rotor axis relative to the airframe.

Abstract: According to one aspect, a controller, including a processor, sets an initial vibration frequency to be applied to an airframe. The controller commands one or more force generators to apply a vibratory load to the airframe at the initial vibration frequency. The controller determines a vibration response of the airframe at the initial vibration frequency using sensors. The controller sweeps through a range of vibration frequencies to be applied to the airframe. The one or more force generators are commanded to apply a plurality of vibratory loads to the airframe over the range of vibration frequencies. The controller determines a range of vibration responses of the airframe over the range of vibration frequencies using the sensors. A global stiffness of the airframe is determined based on the vibration response and the range of vibration responses. The controller reports results of the determined global stiffness of the airframe.