A method of data collection from a rotor system of an aircraft includes positioning a plurality of sensors at a plurality of locations of a rotating portion of the rotor system. One or more antennae are located at one or more rotationally fixed locations of the aircraft. Rotor system data is collected via the sensors and is wirelessly transmitted from the sensors to the antennae and is transferred from the antennae to a gateway where it is normalized and synchronized. In another embodiment, a data collection system for a rotor includes a plurality of sensors located at rotating locations of the rotor, the sensors configured to collect and wirelessly transmit rotor data. Antennae are located at a fixed location of the aircraft. The antennae are configured to send and receive data from the sensors. A gateway is connected to the antennae to normalize and synchronize the rotor data.

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

An aircraft rotor blade includes a surface of the rotor blade, at least one main hole that extends through the surface and has a width and a length, and at least one leader hole that extends through the surface and has a length that is less than the length of the main hole and arranged spaced from and adjacent the main hole. The leader hole gradually increases in width from a first end of the leader hole opposite the main hole to an opposed second end of the leader hole proximate the main hole to operatively gradually distribute stress in the leader and main holes and rotor blade and reduce an amount of the stress exerted therein.

A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe, the translational thrust system including a propeller. A gearbox system is operably connected to the main rotor assembly and the propeller to drive rotation of the main rotor assembly and the propeller. The gearbox is configured to maintain a main rotor assembly tip speed below Mach 0.9 and a propeller helical tip speed below Mach 0.88.

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.

The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

In an embodiment, an apparatus includes: a gearbox including: a housing having an opening; an input pinion disposed in the housing; a moving feature mechanically coupled to the input pinion, the moving feature and the input pinion being operable to convert between power and torque; and first sensors disposed on the moving feature, the first sensors having batteries, where the moving feature is operable to rotate about a common axis, each of the first sensors being exposed by the opening as the moving feature rotates about the common axis.

The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

An adjustable balance module for the balancing of rotatable blades. The adjustable blade balance module includes a frame that retains and covers an adjustment screw with a mass that translates along a threaded shaft of the adjustment screw. The adjustment screw is incrementally controlled by an adjustment dial that is accessible from an exterior surface of the blade.