Abstract: According to some embodiments, a rotorcraft includes a secondary rotor control system located proximate to the empennage of the rotorcraft. The secondary rotor control system includes at least one hydraulic pump and at least one hydraulic actuator. The at least one hydraulic pump is located proximate to the empennage. The at least one hydraulic actuator is located proximate to the empennage and configured to adjust at least one operating characteristic of the at least one secondary rotor blade.

Abstract: According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rudder system, and an anti-torque control system. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade. The anti-torque control system is operable to receive a request to change an amount of anti-torque force applied to the body, compare a rotorcraft performance parameter to a threshold value, instruct one of the anti-torque rotor system or the anti-torque rudder system to change the amount of the first force if the rotorcraft performance parameter is less than the threshold value, and, if the rotorcraft performance parameter is greater than the threshold value, instruct the other of the anti-torque rotor system or the anti-torque rudder system to change the amount of the second force.

Abstract: According to one embodiment, a landing point indication system includes an image provider, a rotorcraft position provider, a pilot image generation system, and a display device. The image provider is operable to provide a visual representation of an area underneath a rotorcraft. The rotorcraft position provider is operable to provide information indicating a position of the rotorcraft. The pilot image generation system is operable to generate a supplemented visual representation. The supplemented visual representation includes the visual representation of the area underneath the aircraft and information indicating a position of the rotorcraft relative to the visual representation. The display device is operable to display the supplemented visual representation within the rotorcraft.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rotor enhancement system, and an anti-torque rudder system. The anti-torque rotor enhancement system includes an aerodynamic structure having an opening therethrough and a support structure coupling the aerodynamic structure to the body of the rotorcraft such that the opening is positioned proximate to a rotation path of the at least one anti-torque rotor blade. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade.

Abstract: A reconfigurable rotor blade system includes an internal mass that is configured to translate in order to produce a spanwise torsional twist of the rotor blade. An actuator is configured to selectively translate the mass so as to relocate a center of mass of the rotor blade. The torsional twist is selectively produced during operation of the rotorcraft.

Abstract: A system and method to detect non-ferrous debris from a non-ferrous roller bearing element. The system includes a trap in fluid communication with a lubrication fluid of the non-ferrous bearing and a sensor operably associate with the trap. The method includes trapping the non-ferrous material debris in the lubrication fluid with the trap and triggering the sensor upon detection of the non-ferrous material debris trapped within the trap.

Abstract: A movable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end and an ingress/egress location at a second end, and a seat that travels along the predetermined path between the operational location and the ingress/egress location, wherein the seat has an operational orientation at the operational location and an ingress/egress seat orientation at the ingress/egress location; the ingress/egress seat orientation being substantially angled relative to the operational seat orientation. Another moveable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end, an ingress/egress location at a second end, and a standby location along the path there between; and a seat that travels along the predetermined path between the operational location, the standby location, and the ingress/egress location; wherein the position of the seat is adjustable at the operational location.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: A method of controlling an audio system includes generating a situation response model for a situation parameter, determining a situation parameter value, and at least one of (1) providing an audio system output as a function of the situation response model and the situation parameter value and (2) receiving an audio system input as a function of the situation response model and the situation parameter value.

Abstract: An engine control system having an engine, a digital engine control, and a gain logic disposed within the digital engine control for use with an aircraft. The digital engine control is configured to receive and process inputs from systems within the aircraft. Gain logic uses the inputs to generate command data to regulate the performance of the engine so as to allow rotor speed deviations from a set point.

Abstract: A lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material; and a structure coupling mechanism; wherein the body prevents friction-related damage to the structure. Another lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material selected from the group consisting of: a polyamide or polyimide impregnated carbon fiber layup, a peek or PEI injection mold with carbon fiber, compression molded carbon fiber or fiberglass, a resin infusion with carbon fiber preform fabric, a fiber reinforced thermoset, acetal resin, machined acetal or thermoplastic, thermosetting plastic, or a metal-matrix composite; wherein the body prevents friction-related damage to a structure.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: A movable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end and an ingress/egress location at a second end, and a seat that travels along the predetermined path between the operational location and the ingress/egress location, wherein the seat has an operational orientation at the operational location and an ingress/egress seat orientation at the ingress/egress location; the ingress/egress seat orientation being substantially angled relative to the operational seat orientation. Another moveable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end, an ingress/egress location at a second end, and a standby location along the path there between; and a seat that travels along the predetermined path between the operational location, the standby location, and the ingress/egress location; wherein the position of the seat is adjustable at the operational location.

Abstract: An engine control system having an engine, a digital engine control, and a gain logic disposed within the digital engine control for use with an aircraft. The digital engine control is configured to receive and process inputs from systems within the aircraft. Gain logic uses the inputs to generate command data to regulate the performance of the engine so as to allow rotor speed deviations from a set point.

Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

Abstract: A reconfigurable rotor blade system includes an internal mass that is configured to translate in order to produce a spanwise torsional twist of the rotor blade. An actuator is configured to selectively translate the mass so as to relocate a center of mass of the rotor blade. The torsional twist is selectively produced during operation of the rotorcraft.