Abstract: An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).

Abstract: An airfoil blade (2) of a bearingless rotor of a helicopter. Said airfoil blade (2) has a pitch axis from a tip end to a root end and said root end is provided with junction means for a separable junction arrangement of said airfoil blade (2) with a flexbeam head (13), and a control cuff (4, 22). Said junction arrangement is mechanical with removable fasteners respectively removable connecting said root end of said airfoil blade (2) to said control cuff (4, 22) and said flexbeam head (13). Said root end comprises at least two openings (7, 8) being asymmetric with regard to said pitch axis.

Abstract: A landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring-mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).

Abstract: A proximity warning system for a helicopter (22) comprising at least two radar units (1-3), preferably three radar units (1-3) arranged to transmit microwaves and receive reflections of said microwaves from obstacles (10). The at least two radar units (1-3) are fixed next to a main rotor head(s) (20) of the helicopter (22) for horizontally scanning an entire environment of 360° around the helicopter (22), all of said at least two radar units (1-3) operating essentially at the same frequency.

Abstract: An air vehicle with a slip protecting and gas sealing composite floor (1, 10) inside a fuselage, particularly a helicopter with a slip protecting and gas sealing composite floor (1, 10) inside a fuselage. Said slip protecting and gas sealing composite floor (1, 10) is built up of a profiled elastomer layer (2) provided at its bottom side with a cross-linking agent, n-layers (3) of a further component or a variety of different components and partially thermosetting resin covered by a profiled elastomer layer (2), a honey comb layer (4) and lower n-layers (5) of said further component or variety of different components and partially thermosetting resin, said honey comb layer (4) being sandwiched between said n-layers (3) and said lower n-layers (5).

Abstract: A detection system and method for detection of damages on at least one rotating component (10, 20, 30. . . N) of an air vehicle caused by at least one solid, comprising measuring means (S1, S2, S3 . . . Sn) for measuring vibration and/or sound of said rotating components (10, 20, 30 . . . N), to acquire the time signal of vibration and/or sound of any of said rotating components (10, 20, 30 . . . N), and processing means (PRO) for comparing said measured vibration and/or sound with a maximum value or an envelope of standard vibration and/or sound stored in a memory (EM1, EM2, . . . EMn) and warning means (WS) for issuing a warning signal when the measured vibration and/or sound exceeds said standard vibration and/or sound. The air vehicle is an airplane or a helicopter, the solid is a projectile, stones, ice-crystals or bird strike, and the measuring means are vibration sensors (S1, S2, S3 . . . Sn) and/or acoustic sensors (S1, S2, S3 . . . Sn).

Abstract: A shock and impact resistant multilayered composite comprising an outer shatter protection body, and at least one active body along side the shatter protection. At least one highly elastic and tearproof absorption/dissipation body is provided along side the at least one active body, said outer shatter protection body being cured to said at least one active body and said at least one active body being cured to said at least one absorption/dissipation body. The present invention relates as well to a method for fabrication of such a shock and impact resistant multilayered composite.

Abstract: The invention is related to an electrical powered tail rotor (1) of a helicopter comprising a housing (2) around the tail rotor (1), and at least one permanent magnet energized synchronous motor with a stator (6, 7) with an increased number of poles (9). Said at least one synchronous motor is integrated as a torus (8) around an opening of the housing (2) encompassing the tail rotor (1). Blades (4) of the tail rotor (1) are fixed to at least one rotating component (10, 11) of said at least one synchronous motor. Supply means provide for electric energy to said at least one synchronous motor. Blade pitch control means are provided at the torus (8).

Abstract: A composite gusset filler (1) of cut-off material from fiber fabrics (2, 3) trimmed into fragments of 2 min-10 mm length, separated into single yarn or roving elements mixed to quasi-homogeneous raw material for a semi-finished gusset filler (1). The present invention relates as well to specific shapes and a method of manufacture of said composite gusset filler (1) and to applications of said composite gusset filler (1).

Abstract: A protection device (10) having a set (11) of protection inflatable members (15, 20, 25) including left and right inflatable lateral means (20, 25) that are suitable for co-operating respectively with the left and right shoulder straps (6, 7), said device (10) possessing an inflator (30) for inflating said protection inflatable members (15, 20, 25). The device includes a headrest (35) carrying a nape airbag (15) of said set of inflatable members (15, 20, 25), the nape airbag (15) including one passage (16, 17) per inflatable lateral means (20, 25) in order to convey fluid to each inflatable lateral means (20, 25), said headrest (35) being provided with a hollow support (40) carrying said inflator (30) and with a fluid diffusion box (50) arranged in the nape airbag (15) so as to convey a fluid from the inflator (30) to the nape airbag (15) and to the inflatable lateral means (20, 25).

Abstract: A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.

Abstract: A counterbalanced control stick system for a vehicle comprising: a shaft (2) rotationally mounted in a casing (22) and a joystick (1). Said joystick (1) is pivotably mounted and has a handgrip section (23). The opposed section of said joystick (1) is linked by said resilient means (10, 10.2) to adjustable fixing points (11.1). A plate (11) is provided offset from the joystick (1) is movable relative to said casing (22). The adjustable fixing points (11.1) are controlled by said movable plate (11). An angle sensor (7) is provided for detection of any angular moves of the shaft (2). Electronics (25) are provided to which signals generated by the rotation angle sensors are supplied. The signals are digitized and differing detected values are harmonized.

Abstract: The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor.

Abstract: A planetary gear (1, 20, 30, 40) for variable transmission, particularly a planetary gear for variable transmission towards a tail rotor of a helicopter. At least one gear set (s1, s2, s3, s4) of a sun gear (w4, w6, 21) comprises a ring gear (w1, w7), planetary wheels (2, 22, 32) and a planet carrier (w2, w3, w8). At least one clutch (k, K1, K2) and at least one freewheel (Fl, FL1, FL2) are provided for at least two different speeds of the planet carrier (w2, w3, w8) as output.

Abstract: The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.