Abstract: A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.

Abstract: A rotary winged aircraft includes an airframe and a drive system located at the airframe. A main rotor system is positioned at the airframe and is operably connected to the drive system to provide lift for the rotary winged aircraft. An auxiliary propulsor is located at the airframe and includes a plurality of propeller blades rotatable about a propulsor axis. Collective and cyclic pitch input applied to the auxiliary propeller blades increases yaw performance of the aircraft. A method of operating a rotary wing aircraft includes powering an auxiliary propulsor secured to an airframe of the aircraft and including a plurality of propeller blades rotatable about a propulsor axis. Individual propeller blades are cyclically rotated about their respective propeller blade axes to cyclically change a propeller blade pitch. Rotation of the aircraft about a yaw axis is induced via the collective and cyclic pitch change of the propeller blades.

Abstract: A bond fixture including a plurality of supports mounted about a surface. At least one of the plurality of supports includes a vertical member and a hand crank operable to adjust a position of the vertical member. A first fixture is disposed at an end of the bond fixture and is movable relative to the surface. The first fixture includes a base and a support extending from the base. A second fixture includes a first member and a second member movably coupled. A fastener extending between the first member and the second member controls relative movement of the first member and the second member to define an opening there between. Each of the first member and the second member includes a plate having a heater formed therein.

Abstract: Systems and methods for controlling aircraft obtain at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement data of the aircraft. A round-referenced heading of the aircraft is obtained and a heading error is calculated based on a difference between the ground-referenced heading and a target heading. A lateral movement error value is generated based on at least one of the ground-referenced longitudinal movement data and ground-referenced lateral movement data, and based on the heading error.

Abstract: A propulsor hub is provided and includes a casing including an inner annular part and blade-connection parts extending outwardly from the inner annular part, a liner having inner and outer opposed radial ends, the liner being disposed about a corresponding one of the blade-connection parts with the inner radial end thereof at a distance from the inner annular part and a weighted element securely disposed about the corresponding one of the blade-connection parts to abut the outer radial end of the liner.

Abstract: A heater mat assembly for a rotor blade spar is provided including a plurality of electrically conductive heater wires extending in a spaced parallel configuration along a path of the rotor blade spar. An electrical current is flowed through the plurality of heater wires to inhibit ice accumulation on a portion of the rotor blade spar. At least one layer of a first insulating material is arranged adjacent a first side of each of the plurality of heater wires such that the at least one layer of the first insulating material is disposed between the plurality of heater wires and an adjacent surface of the rotor blade spar. The first insulating material comprises a thermally and electrically insulating material.

Abstract: A box frame hub arm structure is provided and includes a body having an outboard surface, which is disposable to abut with an inboard surface of an outboard arm of an aircraft rotor head, and lead/lag sides. The body is formed to define a first cavity, an aperture communicative with the first cavity through the outboard surface and second and third cavities. The second and third cavities extend outwardly in opposite lead/lag directions from the first cavity to the lead/lag sides.

Abstract: A method for imaging a moving object includes scanning a predetermined area with at least one distance sensor to form an image of a structure of a moving object using a safe sensing time window to periodically refresh the image. The images of the structure are compared to a known model of the structure to estimate rates of motion. A refined time window is determined based on the estimated rates of motion to monitor the moving object with increased accuracy and/or range compared to the safe time window.

Abstract: A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

Abstract: An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

Abstract: An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.

Abstract: A system for detecting icing includes an optical sensor configured to view at least a portion of an exterior surface or component of an aircraft and to output sensor data indicating at least one optical quality of the exterior surface or component, and an icing detection module. The icing detection module is configured to receive the sensor data from the optical sensor, compare the sensor data to predetermined quality data indicating at least one known optical quality of the exterior surface or component without icing, and determine the presence of icing on the exterior surface or component based on a difference between the sensor data and the predetermined quality data.

Abstract: In accordance with at least one aspect of this disclosure, a structure can include a body, and one or more thermal sheet sensors disposed on or within the body. The one or more thermal sheet sensors can be configured to receive heat from the body to allow sensing of thermal flux through the body to monitor and/or determine a condition of the structure.

Abstract: A fluid distribution assembly for distributing a fluid, the fluid distribution assembly includes an inlet housing including a first conduit and a bypass conduit; a chip detector cavity in fluid communication with the first conduit such that the fluid can pass through the first conduit into the chip detector cavity; and an outlet housing in fluid communication with the chip detector cavity and the bypass conduit such that the fluid can pass into the outlet housing through the chip detector cavity and/or the bypass conduit.

Abstract: 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.

Abstract: According to an aspect of the invention, a method of optimal safe landing area determination for an aircraft includes accessing a probabilistic safe landing area map that includes a plurality of probabilistic indicators of safe landing areas for the aircraft. A processing subsystem that includes one or more processing resources generates a list of candidate safe landing areas based on the probabilistic safe landing area map and one or more constraints. At least two of the candidate safe landing areas are provided to a path planner. The list of candidate safe landing areas is ranked based on results from the path planner indicating an estimated cost to reach each of the candidate safe landing areas. Based on the ranking, an indicator of an optimal safe landing area is output as a desired landing location for the aircraft.

Abstract: A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.

Abstract: A tool system is provided and includes a securing element, a hammer element configured to drive a member toward the securing element and first and second orientation elements rigidly disposed on the securing and hammer elements, respectively. The securing and hammer elements have respective operational axes and the first and second orientation elements respectively include orientation sensors configured to cooperatively determine a relative orientation of the respective operational axes.

Abstract: A gearbox housing of an aircraft includes a surface configured to contact with and support a load of a component of the aircraft such that the surface is susceptible to corrosion. The surface has an area from which a portion of material was removed. A structural deposit is formed by cold spraying one or more layers of powdered material within the area. The structural deposit is configured to share the load applied to the surface by the component.