One embodiment described herein is a damper for a rotor system, the damper comprising a cylindrical housing having a hollow interior; a piston disposed within the hollow interior and extending along a central axis of the housing; a first attachment member disposed on a first end of the damper and connected to the housing; a second attachment member disposed on a second end of the damper and connected to the piston; and a conductive cover wrapped around a portion of an exterior surface of the housing between the first attachment member and the second attachment member.

The invention relates to an electronic display device on board an aircraft capable of landing or maintaining a hover above a landing zone and comprising: a module for calculating a distance between the aircraft and the landing zone according to a horizontal direction and for determining a height of the aircraft; and a module for displaying an exocentric aircraft symbol, positioned at a distance said exocentric from the aircraft according to an exocentric direction and at a height difference said exocentric relative to the aircraft, the display module being further configured to display an exocentric landing zone symbol, positioned at a distance from the landing zone equal to the exocentric distance according to the exocentric direction and at the same height as the exocentric aircraft symbol.

A control system for a multi-rotor aircraft is described that results in lower operating noise. Allowing blades to flap during flight reduces aerodynamic interference as blades pass by other aircraft components, such as wings or the fuselage. Pitch links coupled to a rotational swashplate can be used to allow flapping during flight. The swashplates can allow the canting of the rotors to change a rotational or out-of-plane angle of the blades to decrease noise.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

Embodiments herein describe mitigating flexible modes in an airframe of an aircraft by operating a battery for the aircraft as a tuned mass damper. One embodiment comprises an Unmanned Aerial Vehicle (UAV). The UAV includes a flexible airframe, a plurality of propulsors coupled to the flexible airframe that generate thrust for the UAV, a battery that provides electrical power for the plurality of propulsors, and a suspension system that suspends the battery from the flexible airframe and operates the mass of the battery as a tuned mass damper to dampen flexible modes generated in the flexible airframe during flight.

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

Aspects of this disclosure relate to a custom aircraft door mounting system that employs a vertical rolling motion enabled assembly, comprising: a first fitting configured to be mounted to an overhead structure of an aircraft, the first fitting including a cam follower slot formed within the first fitting; an elastomeric bearing pivotally coupled to a second fitting; and a cam follower coupled to the elastomeric bearing, the cam follower being configured to slide vertically within the cam follower slot to accommodate relative motion between the second fitting and the overhead structure of the aircraft.

An assembly for an aerial system includes a wing support foldably connected to a first and second side of a body of the aerial system, a protection structure coupled to the wing support and disposed over propellers coupled to the wing support, wherein at least one of the protection structure and the wing support includes at least one of a positioning hook and a positioning groove, wherein the protection structure and wing support are fixed relative to each other with the at least one of the positioning hook and the positioning groove.

An exemplary tiltrotor aircraft includes a fuselage carrying a wing, a pylon assembly coupled to the wing such that the pylon assembly is rotatable to selectively operate the tiltrotor aircraft between a helicopter mode and an airplane mode, a vibration isolator assembly connected to the pylon assembly and the wing including a first vibration isolator configured to isolate vibration in a vertical plane a second vibration isolator configured to isolate vibration in a lateral plane.