Abstract: A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.

Abstract: A pyrotechnic circuit breaker (1), comprising a body (2), an igniter (4), a piston (5) and a bus bar (6), wherein the igniter (4), the piston (5) and the bus bar (6) are adapted to be accommodated within the body (2), and wherein the piston (5) comprises a cutting edge (51) and is adapted move along a normal direction (Z-Z) to cut a portion (61) of the bus bar (6), thereby separating the bus bar (6) into a proximal portion and a distal portion in order to break a circuit, wherein the cutting edge (51) of the piston (5) is stepped so that the portion of the bus bar (6) is cut sequentially, in at least two successive cutting operations along the movement of the piston (5) from a raised position to a lowered position, characterized in that the bus blade (6) comprises a breakable portion (61) configured to be cut by the cutting edge (51) of the piston (5), wherein said breakable portion (61) comprises slots (62) in order to divide the breakable portion (61) into multiple sub-portions (61a, 61b, 61c) that are adap

Abstract: The invention relates to the field of feeding devices, in particular for feeding rockets on the ground. A feeding device (4) of the invention comprises at least two mutually complementary feeding connectors (5, 6), a breakable connection member (15) connecting these two feeding connectors (5, 6) together and presenting a breakable section (15c) between these two feeding connectors (5, 6), and a force transmission member (16) connected to said breakable section (15c) in such a manner as to transmit a breaking load thereto in order to unlock the connection between the two feeding connectors (5, 6). During unlocking, a breaking load transmitted by the force transmission member (16) thus serves to break the breakable section (15c).

Abstract: An aircraft aerodynamic surface includes a torsion box having an upper skin, a lower skin, and a front spar, and a leading edge having an external shell and an impact resisting structure. The external shell may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure is spanwise arranged between the external shell and the front spar, and is configured for absorbing a bird strike to prevent damage in the front spar. Also, at least one of the external shell and the impact resisting structure is fitted with the upper and lower skins of the torsion box to thereby facilitate leading edge exchange.

Abstract: A fiber application tool for a fiber application process designed, in particular, as an AFP, has a fiber contact surface area, which has a fiber contact surface for applying and/or pressing the fibers onto a work surface. The tool further includes an activation device for activating an adhesive, matrix, resin, or binder material provided at the fibers by means of an activation radiation so that the fibers are tacked onto the work surface. The fiber contact surface area for the activation radiation may be transparent and that the activation device may be designed so to guide and/or deliver the activation radiation through the transparent fiber contact surface area to the fibers to be pressed by the fiber contact surface.

Abstract: A phase angle can be measured between an analog signal and a reference signal by converting the analog signal to digital samples in a residue number system (RNS) analog-to-digital converter (ADC), based on a RNS scheme. The phase angle can be measured directly from the RNS values output by the RNS ADC, or the RNS values can be converted to a binary scheme, such as straight binary, offset binary or two's complement, before calculating the phase angle measurement.

Abstract: A fairing has a molded body and an electrical wire embedded therein. The body may be constructed from a molded plastics material or a composite material.

Abstract: A rotor drive for a tail rotor of a helicopter is provided. The system includes a stator and a rotor mounted to the stator with a rotatable central carrier. Rotor blades are radially attached to the rotatable central carrier and each of the rotor blades is pivotable about their respective radial central axis for variation of blade pitch. At least one permanent magnet is provided on each rotor blade. A plurality of electromagnets is provided on the stator close enough to allow inductive interaction between the plurality of electromagnets and the at least one permanent magnet on each rotor blade. The permanent magnets are offset from the radial central axis in a direction perpendicular to the rotation plane for individual pitch control of the rotor blades by individual control of electric supply to the electromagnets.

Abstract: A system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes a first adapter member, a second adapter member and a connector member. The first adapter member has a first mating portion configured to substantially conform with a profile of a first component of the structure in more than one plane. A first attachment portion is connected to the first mating portion. The second adapter member has a second mating portion configured to substantially conform with a profile of a second component of the structure in more than one plane. A second attachment portion is connected to the second mating portion. The connector member securely interconnects the first and second attachment portions of the first and second adapter members. A related method of interconnecting components in a vehicle body structure is also disclosed.

Abstract: A vehicle seat comprising a stand and a bucket having a seat pan and a seat back. Said stand serves to fasten said bucket to a floor of said vehicle and to absorb deformation of said floor while limiting the mechanical stresses that are transmitted to said bucket. Said pan is connected to said bucket via a revolute joint for pivoting about a transverse direction and by energy absorber devices. The stand has two first legs forming a fork and connecting the front of said bucket to said floor via ball joint connections. The bucket is connected to said floor at the rear of the seat via two ball joint connections. The stand is thus connected to said bucket via three points and to said floor via four points making it possible to avoid twisting said bucket as a result of deformation of said floor.

Abstract: An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

Abstract: A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

Abstract: An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position.

Abstract: A system for navigating an aircraft includes a first aircraft with a first communication unit and a second aircraft with a second communication unit. The first aircraft is adapted for determining coordinates of a position of a waypoint. The first communication unit is adapted to transmit the coordinates of the position of the waypoint to the second communication unit. The second aircraft is adapted to navigate to the position of the waypoint. Several waypoints can be provided in this manner such that a flight trajectory is established along which the second aircraft may follow the first aircraft. In addition, the second aircraft may be adapted to follow the first aircraft based on a received identification signal. In certain embodiments, the system can be used such that the second aircraft can follow the first aircraft in case of a failure of systems of the second aircraft.

Abstract: A method for defining a parameter value for controlling the transmission power of a set of user equipment served by a cell defined by a base station of a cellular telecommunication network, includes, for the base station, receiving, from the set of user equipment located in the cell, a set of attenuation values including, respectively by piece of equipment, an attenuation value of a signal transmitted by the base station and received by the piece of user equipment and, if the piece of user equipment is also located in a non-serving cell, an attenuation value of a signal transmitted by the base station of the non-serving cell and received by the piece of user equipment; determining, from the set of received attenuation values, a value of a parameter for controlling the transmission power; and sending, to the set of user equipment served by the cell, the value of the control parameter.

Abstract: A fastener device provided with at least one movable stud and a stationary stud, the movable stud including first magnetization means that co-operate with second magnetization means of the stationary stud. At least one magnetization means is carried by a ball joint, each magnetization means being carried by movement means that cause the magnetization means to move in translation along a longitudinal axis from an engagement position to a disengagement position in reversible manner, the magnetization means being strongly magnetically attracted to each other when they are facing and each in the engagement position and being magnetically attracted only slightly or not at all when at least one magnetization means is in the disengagement position.

Abstract: A device and to a method for the production of essentially two-dimensionally arched large-area structural components from a fiber composite material, including a jig having a convex mounting surface which has longitudinally extending receiving channels for the insertion of construction components and which can be loaded with auxiliary materials, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the jig includes a mounting shell that at the edge can be elastically deformed inwards, which mounting shell, by way of a plurality of actuators that are articulated to the inside, can be moved between an extended position (A) and at least one retracted position (B) in which the jig can be moved relative to the longitudinally extending receiving channels from the laminating bonding device without undercuts.

Abstract: A method estimates a channel for radioelectric propagation between a transmitter and a receiver. The transmitter transmits a signal including frames that each use N1 frequency subcarriers, over each of which N1 symbols are transmitted, wherein, among the set of symbols, certain symbols, referred to as pilot symbols, are known to the receiver. The method implemented in the receiver includes; determining an overall intermediate covariance matrix M2 of the channel that embodies a time profile of the channel, which profile is symmetrical and centered on the time synchronization position, and a frequency profile of the channel, which profile is symmetrical and centered on the frequency synchronization position; calculating a vector for an intermediate channel C on the basis of the predetermined overall intermediate covariance matrix M2; and estimating the channel on the basis of the calculated vector for the intermediate channel C?.

Abstract: An alignment adjusting device is provided for an optical focal plane assembly, wherein the optical focal plane assembly has a detector with a detector plane and is adapted to be mounted to an optics assembly having an optical focal plane. The alignment adjusting device is adapted for allowing an alignment of the detector plane representing an image area and the optical focal plane. The alignment adjusting device includes a detector support for receiving the detector; a plurality of members, wherein a first member of the plurality of the members is connected to the detector support and a second member is connected to a flange that is adapted to be connected to the optics assembly. The first member, the second member and the remaining number of the members are pairwise moveable connected to each other by a number of springs and/or supporting elements.