Abstract: A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction.

Abstract: An aircraft (1) provided with a main gearbox (3) fastened to a load-bearing structure (2) via at least three suspension bars (5). An active vibration absorber (10) is fastened around each suspension bar (5), each vibration absorber (10) being provided with a first mass (11) connected to the associated suspension bar (5) via first resilient means (21), and with a second mass (12) connected to the first mass (11) via second resilient means (22), said vibration absorber (10) having a force generator (15) interposed between the first mass (11) and the second mass (12) and inputting a control force on being instructed by a control unit (16) as a function of information coming from at least one first measurement sensor (17) for sensing monitoring parameters for monitoring the associated suspension bar.

Abstract: A system and method of minimizing the attitude hump phenomenon of a rotary wing aircraft is provided. The rotary wing aircraft includes upper pitching-stabilizer and at least one lower pitching-stabilizer. The lower stabilizer is positioned in a wake of the upper stabilizer generated by a stream of air passing through the rotary wing and impacting against the upper surface of the upper stabilizer.

Abstract: A method of modifying a helicopter includes providing a tail boom of the helicopter. The tail boom includes a first side located on an opposite side of the tail boom from a second side of the tail boom. A main rotor blade of the helicopter approaches the second side of the tail boom during rotation. The first side and the second side of the tail boom include asymmetrical surface profiles about a vertical plane of the tail boom. The method further includes securing a plurality of vortex generators to the first side of the tail boom.

Abstract: Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device.

Abstract: A suspension device (10) provided with at least one suspension means (20) comprising a flapper (21) performing pendulum motion, the flapper (21) being provided with a mass support (25) supporting at least one flapping mass (30). The mass support (25) is hinged to a carrier structure (2) for isolating and to a holder bar (15) for holding said mechanical assembly. The suspension device (10) includes at least one force generator (70), said suspension device (10) having at least one computer (50) connected to a measurement system (55) measuring the levels of vibration, and to said force generator (70) to regulate said amplitude and said phase actively by controlling the force generator (70) as a function of at least one measurement signal coming from said measurement system (55).

Abstract: The rotorcraft may include an airframe, at least one engine connected to the airframe, and a rotor connected to the airframe. The rotor may include a hub, a rotor blade, and a feathering spindle connected to the hub. The rotor blade may have a root and a tip and form a conduit extending in the radial 5 direction from the root to the tip. The root may comprise a wall forming a hollow circular cylinder. The hollow circular cylinder may form a portion of the conduit. A plurality of bolts may be distributed circumferential within the wall of the root. The plurality of bolts may extend in the radial direction from the wall of the root to secure the rotor blade to the feathering 10 spindle.

Abstract: A system for reducing the transmission of vibration from a first vibrating body to a second body, the system having a first part connected to the first vibrating body, a second part connected to the second body and an electro-hydrostatic actuator connected to the first and second parts, the electro-hydrostatic actuator being operable to continuously oscillate the first and second parts 10 relative to each other at a frequency substantially corresponding to the frequency of vibration of the first vibrating body.

Abstract: A shaft assembly includes one or more axially-arranged plies having a plurality of bundles of strands. Each strand is formed of a ultra-high modulus carbon fiber material. One or more strands of glass fiber are wrapped around each bundle of the plurality of bundles. A volume of resin injected into the one or more axially-arranged plies and the assembly is cured via a resin transfer molding process. A method of forming a shaft assembly includes arranging a plurality of strands of ultra-high modulus carbon fiber material into a plurality of bundles. Each bundle of the plurality of bundles is wrapped with one or more strands of glass fiber material. The plurality of bundles are arranged into one or more axially-extending plies at a mandrel. A volume of resin is injected into the plurality of bundles and is cured to form the shaft assembly.

Abstract: According to one embodiment, a rotor head includes a yoke, a torque-splitter assembly, and a joint assembly. The torque-splitter assembly includes a spine assembly, a first trunion, and a second trunion. The spline assembly is configured to receive the drive shaft through a first opening. The spline assembly has a first plurality of outer splines oriented in a first direction and a second plurality of outer splines oriented in a second direction different from the first direction. The first trunion is disposed about the first plurality of outer splines. The second trunion is disposed about the second plurality of outer splines.

Abstract: A rotary wing aircraft, a rotor blade and a horizon scanning system are provided. The rotary wing aircraft, for example, may include, but is not limited to, a mast, an engine configured to provide rotational force to the mast and a controller. The rotary wing aircraft may further include a rotor blade connected to the mast having a leading edge, a plurality of tubercles positioned on the leading edge of the rotor blade, and a sensor housed within at least one of the plurality tubercles communicatively connected to the controller.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: Provided is an inflatable wing for a rotary-wing aircraft capable of obtaining auxiliary lift by inflating the inflatable wing equipped on the fuselage when a main rotor is in non-powered rotation state by not providing power for rotating the main rotor due to causes such as an engine failure in a conventional type of rotary-wing aircraft having a single engine, thereby providing a safer emergency landing.

Abstract: Apparatus and methods is used for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. A power take-off engages a rotor and is engaged in response to detecting a loss of engine power.

Abstract: A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods are disclosed for thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed.

Abstract: Methods and systems for balancing helicopter rotor blades are disclosed. In some examples, density data of a rotor blade may be acquired by scanning the rotor blade. In some examples, a three-dimensional model of a rotor blade may be merged with density data of the rotor blade. In some examples, simulations may be performed to predict flight data associated with a modeled rotor blade. In some examples, a database may be referenced to predict a desired weight balance of a rotor blade.

Abstract: An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof.

Abstract: An electrically powered of the vertical takeoff and landing aircraft configured for use with a tether station having a continuous power source is provided including at least one rotor system. The vertical takeoff and landing aircraft additionally has an autonomous flight control system coupled to the continuous power source. The autonomous flight control system is configured to operate an electrical motor coupled to the at least one rotor system such that the vertical takeoff and landing aircraft continuously hovers above the tether station in a relative position. The vertical takeoff and landing aircraft also includes a detection system for detecting objects at a distance from the vertical takeoff and landing aircraft.

Abstract: A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver.

Abstract: An aircraft, capable of hovering, having drive means; and at least one exhaust duct connected to an outlet of the drive means to expel the exhaust gas, produced by fuel combustion, from the aircraft. At least part of the exhaust duct has a thermoelectric conversion circuit for Seebeck-effect converting to electric energy the thermal gradient produced between the inside and outside of the exhaust duct by flow of the exhaust gas.

Abstract: The present application relates to a regenerative or hybrid drive system for an aircraft. The drive system includes the use of a power augmentation device to selectively engage the drive system of an aircraft to store power. The power in the power augmentation device being configured to release a power burst to systems within the aircraft to perform critical flight maneuvers.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: A procedure and a device for the determination of current airspeeds [13] of a rotorcraft [2] in a stationary flight regime and/or at low speeds. A calculation system [1] incorporates two pairs of polynomial calculation laws [9] [10] that are executable successively by pairs. A pair of first polynomial laws [9] calculates estimated airspeeds [11], consisting respectively of longitudinal and lateral airspeeds, and is constructed through multilinear regression based on parameters relating to simulated flight points [17] defined by means of a flight simulator [18]. A pair of second polynomial laws [10] calculates the current airspeeds based on the estimated airspeeds [11], and is constructed through multilinear regression based on parameters relating to test-flight points defined by means of test flights [25].

Abstract: A combined fixed and rotary wing aircraft may operate in vertical takeoff mode relying on the rotary wing, exclusively, and may completely change over to flight support by the fixed wing at higher advance ratios. Advance ratios may exceed not only the typical advance ratios of less than 0.5 but may exceed 1, and may even exceed 2. At the higher advance ratios, the rotary wing may be completely unloaded, the aircraft relying on the fixed wing for vertical support and airfoil lift. To maintain stability in the rotary wing, configuration, autorotation must continue. To power autorotation, without presenting a large area and drag, an anemometer-type flap system may selectively open and close to increase drag on the retreating blades, and provide minimum drag on the advancing blades.

Abstract: The invention relates to an aircraft (10) for conveying one or more recording apparatuses, such as recorders, sensors, cameras, infrared cameras, microphones or the like, through the air. For this purpose, the aircraft (10) has one or more rotors (11) which control the flight movement, as well as a holder (12) for the recording apparatus. Moreover, a framework (13) is provided, on which all of the elements can be attached directly or indirectly. The invention now proposes that the framework (13) includes a body (20) with at least four arms (21) bent inward (24), at the ends (22) of which in each case at least one rotor (11) is arranged. Moreover, a bridge (30) is provided which, at its first end (31), comprises a holder (12) for the recording apparatus, wherein a counterweight (34) is provided at its second end (32). The bridge (30) is gimbaled with its center-of-gravity axis (33) via a central module (40) on the center-of-gravity axis (23) of the body (20) (FIG. 1).

Abstract: A rotor blade assembly includes a flex-beam member and a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length. A rotor blade surrounds the flex beam member and extends from the torque tube to a blade tip. A connecting pin assembly secures the rotor blade and the torque tube at the flex-beam member. The connecting pin assembly includes a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade from a first rotor blade side and a second pin member located at a second rotor blade side. A clamping load between the first pin member and the second pin member secures the rotor blade and torque tube to the flex-beam member.

Abstract: A compact vibration reducing apparatus includes a dynamic mass; elastic member which apply elastic force to the dynamic mass so that the dynamic mass vibrates in a parallel to a vibration damping direction; a control mass; an actuator which move in parallel to a length change direction; and a motion direction converting mechanism which moves the control mass to the dynamic mass so that the control mass moves in a vibration damping direction to the dynamic mass through the operation of the actuator. The actuator is supported by the dynamic mass so that the operation direction of the actuator is not parallel to the vibration damping direction.

Abstract: A rotorcraft is disclosed. The rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and at least one rotor blade having a tip jet. The rotorcraft may further include a plurality of compressors for generating compressed air and a network of conduits connecting the outlets of the plurality of compressors with every tip jet of the rotor. The rotorcraft may further include a control system preventing back flow through each outlet of the plurality of compressors.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: A rotor blade for an aircraft includes an airfoil skin, an active element, and an actuator configured to operate the active element. A heat pipe is configured to promote heat transfer from the actuator to the airfoil skin. The heat pipe has a slope gradient such that a centrifugal force generated during rotation of the rotor blade promotes travel of a condensed working fluid within the heat pipe to move from a condenser end of the heat pipe toward an evaporator end of the heat pipe.

Abstract: The invention concerns a life-saving vehicle (10) designed as a hollow body with the form of a sphere or disk essentially flattened along a vertical axis (16) that demonstrates its greatest width in a horizontal plane (15) and which body, composed of an upper part (11) and a lower part (13), limits an internal passenger compartment (25), whereby the body comprises a stabilizing arrangement (12) that stabilizes the vehicle when it is in water, a telescopic arrangement (40), a stabilization means (14) arranged at the lower part, which stabilization means can be displaced in a vertical direction downwards from the lower part through activation of the telescopic arrangement (40). The vehicle, in order for it to travel not only in the air but also in water, comprises: a first and second rotor (52, 17), a motor (55) with an associated transmission (54), a pair of propulsion units (60) and a stabilizing fin (65).

Abstract: A proximity sensor valve includes a housing which defines a fluid inlet and a fluid outlet in communication with a cavity. A plunger pin within the cavity for movement along an axis, the plunger pin movable between an extended position and a retracted position. The plunger pin extends at least partially outward of said housing at the fully extended position. A spool is within the cavity for movement along the same axis as the plunger pin, such that the spool and the plunger pin are movable with respect to each other to control fluid flow between the fluid inlet and the fluid outlet.

Abstract: A rotor system is disclosed for a reactive drive rotary wing aircraft. Rigidity of the rotor is enhanced and play between flight controls and the rotor are eliminated by mounting swashplate actuators to a flange rigidly secured to the mast. Thermal management of the rotor is performed in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. Thermal management of a rotor may be performed by oil and air flow.

Abstract: An aircraft (1) having an airframe (2) extending along an anteroposterior plane of symmetry (P1) in elevation transversely separating a first side (11) of said aircraft (1) from a second side (12) thereof, said aircraft (1) being provided with hoist means (20) including a winch (21) provided with a drum for winding a hoist cable (22), said hoist means (20) including a beam (30) for guiding said cable, said beam (30) extending from a first end (31) constituting an inlet end for said cable (22) to a second end (32) constituting an outlet end for said cable (22). The hoist means (20) have a counterweight (23), said counterweight including said winch (21) that is fastened to said first end (31), said second end (32) being located on said second side (12) while said winch (21) and said first end (31) are located on said first side (11).

Abstract: A flying vehicle comprises an elongated airfoil having a first end and a second end defining a longitudinal axis, the first and second ends further defining an interior opening extending therebetween and terminating at an outlet port proximal the second end; a solid fuel engine includes a fuel combustion chamber proximal the first end of the airfoil; a first manifold is coupled to the fuel combustion chamber and configured to convey a pressurized gas generated by combustion of a solid fuel; wherein the interior opening conveys the pressurized gas from the first manifold to the outlet port proximal the second end and wherein the pressurized gas is exhausted at the outlet port substantially perpendicular to the longitudinal axis of the elongated airfoil, thereby producing thrust which imparts a rotational motion to the airfoil about a center of mass proximal to the first end, for thereby defining a rotor disk.

Abstract: The present invention relates to a friction device (11) for maintaining a control member (2, 8) in a determined position. The device comprises a contact part (16) movable between a declutched stable position and a clutched stable position, and vice versa. The clutched stable position corresponds to a position in which the contact part (16) bears against the control member (2, 8) in such a manner as to establish a determined friction force. An electromechanical drive means moves the contact part (16) between the two stable positions. The device includes remote control means for activating and deactivating the drive means.

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 portable unmanned aerial vehicle or aircraft, capable of being easily carried by a single individual by means of a mounting device, which can be fastened on a belt or strap. The aerial vehicle comprises a wing attached at one end to a fan or turbine assembly. The fan or turbine assembly may be electrically driven, with power supplied by one or more batteries. In flight, the fan or turbine assembly causes the aerial vehicle to rotate around its center-of-mass (COM), with lift provided by the wing as it rotates. A camera is located on the aircraft at or near the COM.

Abstract: A helicopter and aircraft power device has a plurality of fluid inlets on a windward side of a blade housing and a plurality of fluid outlets on a leeward side in a manner that the fluid inlets communicate with the fluid outlets. The path where the fluid flows in the lengthwise direction on the windward side of the blade housing is far greater than the path where the fluid flows in the widthwise direction on the leeward side of the blade housing, generating a very large pressure difference between the leeward side and the windward side. The action of the centrifugal force and a suction force from a suction motor significantly increase the flowing speed on the windward side of the blade and in the fluid passage, generating bigger pressure difference on either sides of the propeller and thus forming more powerful lift force and driving force.

Abstract: According to one embodiment, a helicopter rotor system has a bearing disposed between the drive train and the rotor blade. The bearing comprises an elastomeric material, a housing member coupled to the elastomeric material, and an anti-rotation member coupled to the housing member opposite the elastomeric material. A bearing mount is coupled to the grip and comprises a first opening configured to receive the anti-rotation member of the bearing. The first opening is defined at least in part by a first surface that receives the anti-rotation member and prevents the anti-rotation member from completing a rotation within the first opening.

Abstract: Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

Abstract: A rotor assembly includes a rotor hub rotatable about a central axis including a plurality of rotor hub arms and blade yokes, each blade yoke including yoke arms located at opposing lateral sides of a corresponding one of the rotor hub arms to which the rotor hub arm is operably connected. The rotor assembly further includes blade retention bearings, each blade retention bearing being a single-element bearing disposed at a corresponding one of the rotor hub arms and which is supportive of a corresponding one of the blade yokes. Rotor blades are secured to corresponding ones of the blade yokes.

Abstract: According to one embodiment, a condensation control system features a dew point analyzer, a fluid system, and a condensation control engine. The dew point analyzer provides a dew point temperature measurement of environmental conditions outside a fluid line having a refrigerant flowing therein. The fluid system provides a flow of insulating fluid to an insulation chamber at least partially separating the fluid line from environmental conditions outside the fluid line. The condensation control engine instructs the fluid system to provide the flow of insulating fluid to the insulation chamber at a temperature such that the temperature of the insulating fluid exiting the insulation chamber is greater than the dew point temperature measurement.

Abstract: An integrated hybrid electric power generation system for producing jet thrust, a superconducting direct drive turbine ring motor for vertical lift, multi-megawatt electric current generation and a pulse-phased high power directed energy weapon (DEW). The system is managed electrically, and may be mated directly to a magnetic aerodynamic generation of rotorhead optimized control as a direct drive electric lift-jet thrust rotorcraft system (DDELJTRS) manifesting an all flight managed controls and weaponized electric system in rotorcraft, vertical lift, aerodynamic flight control, directed energy weapon and jet propulsion for forward flight high speed cruise.

Abstract: An emergency pod configured for use with a rotary wing aircraft is provided including a rigid, generally hollow shell. The shell includes a movable portion configured to move between a closed position and an open position. An inflatable raft is arranged within an interior portion of the hollow shell. The life raft is coupled to an inflation mechanism. A first activation device and a second activation device are operably coupled to the inflation mechanism. The first activation device and the second activation device are configured to operate the inflation mechanism to initiation inflation of the life raft when a force is applied thereto.

Abstract: A piloting assistance device (5) comprising a calculation unit (10) and a display unit (20). The calculation unit (10) executes stored instructions to determine at least one thrust margin for a propeller between a current thrust being exerted by said propeller and a threshold thrust corresponding to a negative power limit (Pmin), and to determine a main minimum total ground slope that can be followed by the aircraft in descent as a function of said thrust margin. Finally, the calculation unit presents a main symbol (25) on a display unit (20), the main symbol (25) representing the minimum total ground slope that can be followed by the aircraft (1) in descent, the main symbol (25) appearing superimposed on a representation (21) of the surroundings that exist in front of the aircraft (1).

Abstract: A drip pan apparatus for use in a helicopter includes a drip pan and a frame having a plurality of frame sides and a plurality of frame corners that define an inwardly-facing peripheral surface. A first frame angle is formed between a first inwardly-facing surface and a second inwardly-facing surface. The first frame angle is an acute angle. The drip pan has an outwardly-facing peripheral surface. The outwardly-facing peripheral surface defines a plurality of sides, including a first side and a second side, to cooperate with the inwardly-facing peripheral surface of the frame. A first angle is formed between the first side and the second side. The first angle is an acute angle. A method of installing a drip pan includes modifying at least a portion of a skirt on the helicopter and then securing the frame to one or both of the modified skirt and the helicopter structure.

Abstract: An aircraft component has an exterior surface and a protective nanocoating carried by the exterior surface. An aircraft has an engine, a fuselage, and a component having an exterior surface and a protective nano coating carried by the exterior surface. A method of protecting an aircraft component includes selecting at least one harmful environmental component and applying a protective nanocoating to the aircraft component, wherein the protective nanocoating is configured to protect the aircraft component from the selected harmful environmental component.

Abstract: A fairing (1) for a structural element of a rotorcraft, the fairing including a rear portion (2) that is substantially orthogonal to the longitudinal direction (L) of the aircraft, extending between two spaced-apart trailing edges (3, 4) and thus presenting a determined width, said rear portion (2) closing at least part of the internal volume defined by the fairing (1) and generating aerodynamic drag in forward flight. According to the invention, the rear portion presents, at least at the trailing edges (3, 4), a shape that is perturbed on the streamlines (5) of the air-flow.

Abstract: According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot.