Abstract: A reusable bumper (10) for a rotorcraft (1) suitable for protecting a rear end (3) of said rotorcraft (1). The bumper (10) comprises a resilient outer shell (20) forming a first chamber (11) having a resilient inner shell (30) placed therein and forming a second chamber (12), said outer shell (20) having at least one main orifice (21), said inner shell (30) being provided with management means (50) for managing the pressure that exists inside said second chamber (12) and suitable for enabling said pressure to increase up to a predetermined threshold in order to inform the pilot that the bumper (10) has made contact with the ground (S), and then to enable said pressure to drop in order to absorb energy resulting from said contact.
Type:
Grant
Filed:
August 19, 2010
Date of Patent:
May 7, 2013
Assignee:
Eurocopter
Inventors:
Joseph Mairou, Pierre Prud'Homme-Lacroix
Abstract: The present invention relates to a tail skid (10) for a rotorcraft (1), the tail skid comprising a contact blade (11) extending from a contact first end (11?) towards a second end (11?), said contact first end (11?) being provided with a top face (12) suitable for facing a structure (7) of the rotorcraft (1) and a bottom face (13) suitable for facing towards the ground (2) when said tail skid (10) is fastened to a rotorcraft (1) standing on the ground (2), said bottom face (13) having a first area.
Abstract: An assisted piloting method for an aircraft having at least two engines (2, 3) includes monitoring a set of parameters (Ng, T4, Tq) of the engines. A first limit indicator (10) displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T4, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T4, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.
Type:
Grant
Filed:
September 16, 2010
Date of Patent:
April 2, 2013
Assignee:
Eurocopter
Inventors:
Daniel Chaniot, Olivier Voinchet, Francois-Xavier Gaulmin
Abstract: A seat for a powered aircraft, the seat comprising a bucket (2) that is supported in hyperstatic manner on a stand. Leg members (7, 8) carry the bucket (2) via bolts (10). A first hinged mechanism for geometrically compensating deformation of the floor associates a ball-joint mounting of the bolts (10) on the leg members (7, 8) with an axial deformation arrangement of the bolts (10) between opposing axial bearing surfaces where they press against a strength member (9) of the bucket (2) and against the leg members (7, 8). A second energy-absorber mechanism associates fuses (22) with deformable support members (23) for the bucket (2), which members engage the bolts (10) and the leg members (7, 8) via slides (25) arranged to adjust the initial height position of the bucket (2).
Abstract: An ejection system for a window pane or panel which is affixed to a frame structure with at least one clamping seal. The system has means for ejecting the panel or window pane from the clamping seal and (a) a frame part with a housing which surrounds the inner face of the window pane or panel along a peripheral path, wherein the housing has an open end facing the window pane or panel; (b) an inflatable seal arranged in the housing; (c) a pressure source which is joined to the inflatable seal; and (d) an emergency actuation means to release pressure from the gas pressure source. The released air or gas expands the inflatable seal which pushes the window pane or panel out of the clamping seal.
Abstract: The present invention relates to an on-board device for measuring the mass and the position of the center of gravity of an aircraft having a plurality of landing gears (T1, T2), each landing gear (T1, T2) being provided with at least one contact member (2) having a deformable element (3) that is deformable under the action of the weight of the aircraft when the aircraft is standing on a surface, and is remarkable in that the formable element (3) is provided with a bar (4) having an eddy current sensor (6) at its free end.
Abstract: The invention provides a method of assembling together two thin plane parts (1, 2) by friction welding. A main sheet (19) made of a material having high thermal conductivity is held against the parts (1, 2) for assembly. The main sheet (19) picks up the heat induced by the friction of a welding pin (5) against the parts (1, 2) for the purpose of forming the weld bead (17), and it dissipates this heat by radiation. Temperature regulation of the welding operation is obtained by the main sheet (19), ensuring that no localized excess heating occurs in the welding zone. The main sheet (19) is based on copper and presents a thickness that is less than the thickness of the parts (1, 2).
Abstract: A drive device (D) for driving first and second lift rotors (2, 3) of a twin-rotor rotorcraft, includes link elements provided with first and second transmission shafts (5, 6) for synchronizing the first and second transmission members (74, 84) of first and second main gearboxes (7, 8), the first main gearbox (7) being provided with first power combiner element (73) firstly meshing with the first transmission member (74) and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6), and the second main gearbox (8) being provided with second power combiner element (83) firstly meshing with the second transmission member (84), and secondly mechanically linked with the first transmission shaft (5) and with the second transmission shaft (6).
Abstract: A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque.
Type:
Grant
Filed:
May 19, 2009
Date of Patent:
March 12, 2013
Assignee:
Eurocopter
Inventors:
Bernard Gemmati, Philippe Vincent, Romuald Biest
Abstract: The present invention relates to a method of flying safely and at low altitude in an aircraft, in which method unsafe relief (R0) of terrain is determined as is the position of at least one high point (4, 5) representing an obstacle (4?, 5?) overlying said unsafe relief (R0). A main volume (V0) is added to said unsafe relief (R0), the main volume being defined between a main volume base (2) placed on the unsafe relief (R0) and an envelope (1), thereby obtaining safe relief (R1) for overflying that contains at least said unsafe relief (R0) and said main volume (V0), said main volume base (2) having an area (2?) defined by a closed peripheral curve (3) resting on said unsafe relief (R0), said envelope (1) being generated using a moving segment (S) of predetermined length (L) extending from said high point (4, 5) to a second point (3?) moving along said peripheral curve (3).
Abstract: A method of determining a sound nuisance level outside an aircraft, wherein an aircraft is fitted with a plurality of external microphones, then during a flight of the aircraft, sound levels are measured using on-board microphones and at least two components are measured of the speed of the aircraft relative to air, and thereafter the kurtosis of samples of the sound level measurements is calculated and a model is determined of variations in a sound nuisance level as function of the air speed components, with the sound nuisance level being determined as a function of the kurtosis.
Abstract: A device for controlling vehicles having a manual control unit configured to influence the direction of movement of a vehicle. The manual control unit provides, in a neutral position of the manual control unit, a trim point to determine a preferred direction of movement. The device further includes a force generating device, generating at least one force acting in the direction of the neutral position of the manual control unit; a trim coupling operable to reduce the at least one force acting on the manual control unit; and a trim control unit configured to store and retain the trim point existing prior to an operation of the trim coupling.
Abstract: A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.
Type:
Grant
Filed:
May 5, 2010
Date of Patent:
February 19, 2013
Assignee:
Eurocopter
Inventors:
Bernard Gemmati, Nicolas Queiras, Paul Eglin
Abstract: A hydraulic valve assembly includes a hydraulic valve, a control rod configured to be moved in translation along a first longitudinal axis by flight controls of an aircraft, a servocontrol, and an outlet rod configured to be moved in translation along a second longitudinal axis and configured to transfer a hydraulic fluid between the servocontrol and the hydraulic valve. A blocker device is configured to block a movement of the control rod when a difference between a first movement of the control rod and a second movement of the outlet rod exceeds a predetermined threshold and includes at least one moveable abutment configured to block the movement of the control rod when the predetermined threshold is reached and configured to move in longitudinal translation with the outlet rod, and a differential lever configured to mechanically link the control rod to the outlet rod and to cooperate with the at least one moveable abutment.
Abstract: A method of fabricating a panel (1) comprising a core (10) made of honeycomb material provided with a plurality of cells (13) and encased by top and bottom outer walls (20, 30), which method comprises, during a preparation stage (P1): fabricating the top outer wall (20); fabricating the bottom outer wall (30); fabricating said core (10), and perforating one internal orifice (11) per fastener element (50) in said core (10) so as to provide a space (12) for receiving said fastener element (50); and then coating at least one layer of a film of an intumescent adhesive (60) on a connection side wall (51) of said fastener element (50) that is to be connected to said core (10). After performing an assembly stage on a bench (70), the assembly comprising the top outer wall (20), the core (10) provided with said fastener element (50), and the bottom outer wall (30) is polymerized in order to obtain said panel (1) provided with said fastener element (50).
Abstract: The invention relates to a method of processing an image sensed by an image sensor on board an aircraft fitted with an obstacle-locator system, in which the position and the extent of a zone in the sensed image, referred to as the zone of interest, is determined as a function of obstacle location data delivered by the obstacle-locator system, after which at least one parameter for modifying the brightness of points/pixels in said zone of interest is determined to enable the contrast to be increased in said zone of interest, and as a function of said modification parameter, the brightness of at least a portion of the image is modified.
Abstract: The invention relates to a door lock comprising a door catch system for double door-type helicopter doors that can, when being closed, additionally be displaced perpendicularly to the plane of the door opening into the closed position (flush fitting). Said door lock comprises a catch element (30) associated with the latch element (31) and actively linked therewith, said catch element maintaining the door ‘caught’ directly in front of its locked position when the door is manually closed until the door is translated to its final closed position via the latch element (31).
Abstract: A method of assisting the piloting of an aircraft (60) at low altitude over terrain (S), in which method, during a first stage, a framework (10) is constructed from at least one main segment (40) and during a second stage a setpoint flight path (50) is constructed. More precisely, during the first stage, said main segment (40) is subdivided automatically into a plurality of secondary segments (41, 42, 43), each of said secondary segments (41) being situated at the same setpoint height above the highest point of the underlying terrain, with two adjacent secondary segments (41) being in alignment or connected together by a bar (44) that extends vertically in a vertical section.
Abstract: An air intake (2) for a turbine engine, and a method implemented by the air intake (2) are disclosed. The air intake (2) is provided with a filter system (10) including foldable filter elements (11), arranged at the inlet section (3) of the air intake (2). In addition, the filter system (10) includes control elements (11) that exert a force along a first direction (Y) on the free end (11?) of the foldable filter elements (11) to adjust the filtering power of the filter system (10), guide members (12) of the filter system (10) serving to guide the movement of the free end (11?) induced by the control elements (13).
Abstract: The present invention relates to an energy absorber device (1) for damping the movements of a load support (2) relative to a stationary base (3), the load support being connected to the stationary base (3) via a hydromechanical connection. The device includes automatic and self-contained setting elements serving firstly to adapt under static conditions to the weight of the loads supported by the support (2), and secondly under dynamic conditions, e.g. in the event of a sudden movement of the crash type, to subject the subassembly including the support (2) and the loads to acceleration or deceleration values that are below a threshold value.