Abstract: An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.

Abstract: A compound helicopter with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the at least one main rotor being arranged in an upper region of the fuselage, wherein at least one propeller is provided that is at least adapted for generating forward and/or backward thrust in operation. The at least one propeller is mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing and at least one lower wing. An upper stub wing arrangement is provided in the upper region of the fuselage, the at least one upper wing of the fixed wing arrangement being mounted to the upper stub wing arrangement.

Abstract: An aircraft having an airframe including a hollow structure referred to as a “storage” structure, the storage structure having an opening that is open to the outside of the aircraft. A sealing device extends around the opening, the sealing device including at least one compressible gasket. A plurality of non-removable fittings are fastened to the storage structure. At least one removable storage shell comprises at least a covering configured to close the opening while compressing each gasket. Removable fittings of the storage shell are attached in reversible manner to the non-removable fittings by respective elongate fasteners passing through each removable fitting and the non-removable fitting.

Abstract: A method of optimizing sections of a tail boom for a rotary wing aircraft, and also to a tail boom including such sections. The method comprises the step of creating a database characterizing standard sections for a tail boom that give precedence to minimizing a negative lift and/or to increasing a lateral force generated by the air stream from the main rotor of the aircraft flowing over the tail boom, a step of establishing looked-for aerodynamic and structural characteristics for said tail boom, and a step of defining the sections of the tail boom as a function of the standard sections and of the looked-for aerodynamic and structural characteristics. The tail boom as defined in this way optimizes the reduction in the negative lift and/or the increase in the lateral force generated by the air stream from the main rotor.

Abstract: A method and a device for avoiding an object by detecting its approach to an aircraft. After detecting an object in the vicinity of an aircraft and detecting its approach, a first track for the object and a second track for the aircraft are estimated from successive first states for the object and successive second states for the aircraft. Thereafter, a minimum distance (dm) between the first track and the second track is estimated and a warning is triggered as soon as the minimum distance is less than a first threshold so as to warn a crew of the aircraft of a risk of collision. Finally, if the minimum distance is less than a second threshold, an avoidance maneuver is performed automatically by the aircraft in order to move away from the first track, and thereby avoid any risk of collision with the object.

Abstract: A vibration damping device equipped with a resonator mechanism comprising at least one resonator, the at least one resonator having a first beater extending from an embedded end to a free beating end. The resonator consists of an elastically deformable base equipped with a first branch and a second branch connected by a central section, the embedded end being embedded at the first branch, the first branch extending from a first end to a second end each rigidly fastened to a mount, the second branch extending from a first end section to a second end section each rigidly fastened to a vibration source.

Abstract: A bracket (24) for connecting a traverse (20) of a landing gear to a cabin of a helicopter. A landing gear retainer (5) is fixed around the traverse (20) coaxially to the longitudinal direction of the traverse (20) and at least one cabin clamp mount (7) is fixed to the cabin. The landing gear retainer (5) is in between the cabin and upper and lower pendulum bolts (12, 13) and upper and lower pendulum bearings (18, 19). A pendulum (9) is in longitudinal direction of the traverse (20) hinged to the landing gear retainer (5). The invention is further related to an application of such brackets (24).

Abstract: A method for optimizing the architecture of the power supply of a load, includes the following steps: determination of a mission profile (16) sizing according to the power required by the load over time; definition of the sources of energy storage for hybridization; association of a characteristic behavior model with each source of energy storage; determination of the couples of sources of energy storage that can generate the mission profile with a minimum mass; and determination, from the potential couples of sources of energy storage, of the couple with the weakest mass.

Abstract: An electrically or hybrid powered multirotor aircraft with complete redundancy on all of its functions of lift, of propulsion, and of control, the aircraft having optimized energy consumption and comprising: a longitudinal structure having two longitudinal beams; a fuselage fastened to the longitudinal structure; two fixed wings serving essentially to provide the aircraft with lift in cruising flight and arranged at respective ends of the longitudinal structure and in a common first plane; at least six rotors serving essentially to provide the aircraft with lift during stages of takeoff and landing, the rotors being arranged in a common second plane distinct from the first plane and parallel to the first plane in such a manner as not to be situated vertically above or below a fixed wing; and two propulsion propellers. An electrical or hybrid power plant serves to drive the rotors and the propulsion propellers in rotation.

Abstract: A door opening system with a deceleration mechanism may be adapted to control an opening of a door module that includes a door panel and a door frame. Deceleration mechanism may include strap that connects door panel with door frame, spool, and spool. Spool may receive one end of strap, is biased to roll up a first portion of strap, and adapted to perform a first unwinding of the first portion of strap. Spool may receive a second end of strap, is biased to roll up a second portion of strap, and adapted to perform a second unwinding of the second portion of strap from spool. Spool may include a braking apparatus that is adapted to decelerate the second unwinding when a velocity of the second unwinding is above a predetermined threshold.

Abstract: An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

Abstract: A power transmission system having at least one inlet speed-reducing gear and a main speed-reducing gear, each inlet speed-reducing gear comprising an inlet pinion meshing with an inlet gearwheel. The inlet gearwheel is constrained to rotate with a main pinion of the main speed-reducing gear, the main pinion meshing with a main gearwheel. At least one inlet gearwheel is secured to reversible connection means in order to be capable of driving a first additional drivetrain connected to an additional rotor.

Abstract: A plate heat exchanger comprising a plurality of plates having a plane peripheral zone, an inner zone having sinusoidal undulations and two chimneys positioned at two opposite corners of the plates. Modules are formed by assembling two plates that make contact via the undulation troughs and the peripheral zones. The modules are stacked so as to make contact via the inlet and outlet chimneys. Each module may thus deform independently, in particular at the undulation troughs and ridges without transmitting stress to the other modules of the heat exchanger. In addition, the heat exchanger may comprise a tie rod in each inlet and outlet pipe so as to withstand the static pressure of the fluids flowing in the pipes.

Abstract: A method of controlling at least one actuator for controlling an aircraft. The method comprises data acquisition steps performed using at least two mutually distinct sensors, the sensors being suitable for taking mutually distinct measurements of at least one flight parameter of the aircraft. Calculation steps generate at least two mutually distinct control laws for controlling the actuator(s). The control laws are functions of the respective measurements. The method controls the actuator(s) sequentially with a first control law in alternation with a second control law.

Abstract: A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Abstract: A magnetic device for capturing metal wear particles in suspension in a lubrication fluid, the magnetic device being for inserting in a straight-line insertion direction of the magnetic device into a wall of a casing via a through orifice serving to put an inside volume of the casing containing the lubrication fluid into communication with an outside volume outside the casing, the magnetic device presenting a longitudinal axis X, the longitudinal axis X being for putting into coincidence with the direction for inserting the magnetic device into the casing, the magnetic device comprising a permanent magnet suitable for attracting the metal particles and a, presence-detector member for detecting the metal particles attracted by the permanent magnet.

Abstract: A control method for controlling aerodynamic means of an aircraft having mechanically decoupled flight controls enabling the aircraft to be piloted by at least two pilots. The aircraft has at least two control members operated by respective ones of the at least two pilots and each enabling control signals to be generated for causing the aerodynamic means to move relative to an incident air stream. The control method includes piloting logic (“operational” logic). The operational logic includes a dual operating mode in which each control member can control the aerodynamic means. In the dual operating mode, only one of the at least two control members, (the “activated” member), has exclusive control over a full travel amplitude of the aerodynamic means. The other control member, (the “deactivated” member), then is temporarily inoperative on the aerodynamic means.

Abstract: The present invention relates to a method for sharing secure data between players (5) on a net said method comprising a cryptography step for data using an asymmetrical cryptographic method with double keys, each player (5) having at least one said double key. The method includes a step for initializing (STP1) a blockchain that includes an operation for storing, at least one initialization block (26) in the blockchain by a predetermined authority using at least one computer, said at least one initialization block (26) comprising at least one said transaction (36) that includes an identity record (84) of a major player, said authority no longer intervening at the end of the initialization step (STP1) at least outside a reinitialization step of a player.

Abstract: A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.

Abstract: A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor that is adapted for controlling a servo-assisted control unit of a vehicle control system, wherein the artificial force feel generating device comprises at least one force generating device that is mechanically connected to the inceptor for generating a tactile cue force acting in operation on the inceptor, and wherein a safety device is provided for limiting authority of the at least one force generating device, the method comprising at least the steps of: monitoring usage of the safety device during operation of the artificial force feel generating device, determining a current accumulated fatigue of the safety device on the basis of the monitored usage, and re-configuring the at least one force generating device on the basis of the current accumulated fatigue.