Abstract: An inside vessel arrangement (5) is fixedly secured in a stator hollow structure (8) and has at least one enlarged static circumference housing (20), and an aerodynamic outer toroid spoiler (18) has an outer external surface (35) complementary to the static circumference housing (20). The aerodynamic outer toroid spoiler (18) radially secured to each of outer tips (23) of rotor blades (10) of a driven rotor system (7). A torus air gap (G) is provided, so that an outer laminar flux (56) is admitted simultaneously with an inlet inner stream (54) and guided through the torus air gap (G), with the inlet main stream and outer laminar flux being converged to merge together in single outlet control airflow (C). The invention typically applies e.g. to vehicles (A) such as aircrafts like rotary wing aircrafts.

Abstract: Obstacle and terrain warning radar system (1) for a rotorcraft (2), the system having at least two assemblies (10), each having at least one radar unit, said rotorcraft (2) including at least one main rotor (20) having at least two blades (22) and a rotor head (23). Each radar unit transmits a centrifugal radar beam (17) with angular beam width in azimuth ? of at least 5° and beam width in elevation ? of at least 5°. Said assemblies (10) of at least one radar unit are positioned directly on said rotor head (23) between said blades (22), said radar system (1) electronically scanning the surroundings with angular coverage in elevation of at least +/?15° and mechanically scanning the surroundings with angular coverage in azimuth of 360°, and then informing the pilot of said rotorcraft (2).

Abstract: An empennage (1.1) of a helicopter comprising a ducted counter-torque device with a multi-blade rotor (4) of rotor blades (3) and optional vertical tail fins (1.2). Flow-straightening stators (5) of stationary vanes are disposed substantially in a star configuration parallel to the rotor plane downstream from the rotor (4). A shroud (2.1) of the ducted counter-torque device is sheathed with a composite structure of an outer erosion protecting surface layer (7.1, 8.1) made of a hard plastic or a plastic composite material, and at least one succeeding layer (7.2, 8.2) of an elastomeric damping material.

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 obstacle information system and method for a helicopter with a warning information processor (3) and a display unit (1) for any obstacle (2) within a predetermined minimum distance d4. Said warning information processor (3) is fed with information related to detected distance d5 and direction of said at least one obstacle (2) detected by an obstacle sensor system (4) to compute and prepare the information for presentation on the display unit (1). Said display unit (1) comprises at least an indication area with a central circular surface (6) and a concentric ring-shaped area (7) around the circular surface (6). Said circular surface (6) is used exclusively for alerts. The ring-shaped area (7) is used for both. Warnings and alerts and the repartition in the indication area of circular surface (6) and ring-shaped area (7) are dependent on the detected distance d5 of said at least one obstacle (2).

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: An air vehicle, particularly a helicopter, includes a slip protecting and gas sealing composite floor inside a fuselage. The slip protecting and gas sealing composite floor is built up of a profiled elastomer layer provided at its bottom side with a cross-linking agent, n-layers of a further component or a variety of different components and partially thermosetting resin covered by a profiled elastomer layer, a honey comb layer and lower n-layers of the further component or variety of different components and partially thermosetting resin, the honey comb layer being sandwiched between the n-layers and the lower n-layers.

Abstract: An optical level sensor mounted to a ceiling of a tank includes a sensor tube. The sensor tube is provided with support and guidance elements extending with at least three radially distributed positions inside the tank. The support and guidance elements collect, support, and guide optical fibers to different heights of the tank. Each optical fiber has a number of input sides and a number of turns forming sensor heads between two input sides, for a different level. The corresponding support and guidance element bends the fiber in the turns forming sensor heads of a small radius r around at least one corresponding guideway.

Abstract: An inside vessel arrangement (5) is fixedly secured in a stator hollow structure (8) and has at least one enlarged static circumference housing (20), and an aerodynamic outer toroid spoiler (18) has an outer external surface (35) complementary to the static circumference housing (20). The aerodynamic outer toroid spoiler (18) radially secured to each of outer tips (23) of rotor blades (10) of a driven rotor system (7). A torus air gap (G) is provided, so that an outer laminar flux (56) is admitted simultaneously with an inlet inner stream (54) and guided through the torus air gap (G), with the inlet main stream and outer laminar flux being converged to merge together in single outlet control airflow (C). The invention typically applies e.g. to vehicles (A) such as aircrafts like rotary wing aircrafts.

Abstract: Obstacle and terrain warning radar system (1) for a rotorcraft (2), the system having at least two assemblies (10), each having at least one radar unit, said rotorcraft (2) including at least one main rotor (20) having at least two blades (22) and a rotor head (23). Each radar unit transmits a centrifugal radar beam (17) with angular beam width in azimuth ? of at least 5° and beam width in elevation ? of at least 5°. Said assemblies (10) of at least one radar unit are positioned directly on said rotor head (23) between said blades (22), said radar system (1) electronically scanning the surroundings with angular coverage in elevation of at least +/?15° and mechanically scanning the surroundings with angular coverage in azimuth of 360°, and then informing the pilot of said rotorcraft (2).

Abstract: A multi-layered transparency (2.1, 2.2) for an aircraft cockpit, particularly a multi-layered window for a helicopter cockpit (1), comprising: one core layer (6) made of a polymer of either PC or mcPA and at least one foil extruded, adhesive interlayer film (3.1, 3.2, 3.3) unilaterally bonded to said at least one core layer (6). At least one outer top layer (5.1, 5.2) made of mcPA, preferably containing additives, is unilaterally attached to said at least one foil extruded adhesive interlayer film (3.1, 3.2, 3.3) distal to said at least one core layer (6) and a scratch resistant outer top coating (4.1, 4.2) is provided unilaterally to said at least one outer top layer (5.1, 5.2) distal to said at least one foil extruded adhesive interlayer film (3.1, 3.2, 3.3). The invention is as well related to a method of producing such a multi-layered transparency.

Abstract: A method for optimized utilization of available energy resources/sources (3) of an electrical system such as for a vehicle generator system. The steps include: determining performance parameters LIst (e.g. current I, voltage U, temperature T, power PD (Pverlust), PE (Pwirk), efficiency, etc.) of a preferred energy resource (3); entering performance parameters LIst (current I, voltage U, temperature T, altitude of the vehicle, etc.) of the energy resource (3) into a thermal model (7); comparing a performance parameter LIst of the energy resource (3) with a specified performance limit parameter LSoll at a specified threshold level; determining a value for an energy reservoir ERest of a preferred energy resource (3); and to calculate a remaining time TMax depending on the energy reservoir ERest of a preferred energy resource (3) and using the one or more identified performance parameters LIst to maintain an operational state of the vehicle.

Abstract: An empennage (1.1) of a helicopter comprising a ducted counter-torque device with a multi-blade rotor (4) of rotor blades (3) and optional vertical tail fins (1.2). Flow-straightening stators (5) of stationary vanes are disposed substantially in a star configuration parallel to the rotor plane downstream from the rotor (4). A shroud (2.1) of the ducted counter-torque device is sheathed with a composite structure of an outer erosion protecting surface layer (7.1, 8.1) made of a hard plastic or a plastic composite material, and at least one succeeding layer (7.2, 8.2) of an elastomeric damping material.

Abstract: A method for detecting electromagnetic threats to an aircraft, wherein electromagnetic fields are measured, and in the case of an arising threat to the aircraft being detected, countermeasures are taken, characterized by the following steps: measuring the frequency and the amplitude of at least one electromagnetic field in the frequency range from 9 KHz to 40 GHz; analyzing the measured results and determining the field intensity in relation to each measured frequency; comparing the field intensity in relation to each measured frequency with stored limiting values or qualification values, wherein the aircraft is qualified for field intensities that are lower than the limiting values; and providing the result in the form of a warning signal in the case of approaching or exceeding a limiting value.

Abstract: An optical level sensor (1) includes: mounting means (11) mounting the sensor (1) to a ceiling of the tank (9); a sensor tube (12, 12.1) provided with support and guidance elements (4) extending with at least three radially distributed positions inside the tank (9) and which collect support and guide optical fibers (3, 3.3, 3.4) to different heights of the tank (9), with each optical fiber (3) having a number of input sides (3.3) and a number of turns forming sensor heads between two input sides (3.3), for a different level (19); the corresponding support and guidance element (4) bending the fiber (3, 3.3, 3.4) in turns forming sensor heads of a small radius r around at least one corresponding guideway (4.3).

Abstract: A rotary aircraft which carries a hanging sling load on at least one support cable, benefits from a stabilizer which generates control signals R to be applied or modulated onto the flight control of the aircraft. At least one sling load pendulum motion detecting unit provides the stabilizer with data on the pendulum motion of the sling load. Additionally, the stabilizer is set up with a working range determination unit S3 for determining the space where free movement is possible in which the rotary aircraft with sling load can move without collision. The stabilizer generates control signals R in dependency of the determined pendulum motion of the sling load and the determined working range.

Abstract: An obstacle information system and method for a helicopter with a warning information processor (3) and a display unit (1) for any obstacle (2) within a predetermined minimum distance d4. Said warning information processor (3) is fed with information related to detected distance d5 and direction of said at least one obstacle (2) detected by an obstacle sensor system (4) to compute and prepare the information for presentation on the display unit (1). Said display unit (1) comprises at least an indication area with a central circular surface (6) and a concentric ring-shaped area (7) around the circular surface (6). Said circular surface (6) is used exclusively for alerts. The ring-shaped area (7) is used for both. Warnings and alerts and the repartition in the indication area of circular surface (6) and ring-shaped area (7) are dependent on the detected distance d5 of said at least one obstacle (2).

Abstract: A method for detecting electromagnetic threats to an aircraft, wherein electromagnetic fields are measured, and in the case of an arising threat to the aircraft being detected, countermeasures are taken, characterized by the following steps: measuring the frequency and the amplitude of at least one electromagnetic field in the frequency range from 9 KHz to 40 GHz; analysing the measured results and determining the field intensity in relation to each measured frequency; comparing the field intensity in relation to each measured frequency with stored limiting values or qualification values, wherein the aircraft is qualified for field intensities that are lower than the limiting values; and providing the result in the form of a warning signal in the case of approaching or exceeding a limiting value.

Abstract: The invention relates to a stabilizer for rotary wing aircraft 11 which carry a hanging sling load 12 in the direction of the ground on at least one support cable 13, and were the stabilizer is set up to generate control signals R to be applied or modulated onto the flight control of the rotorcraft 11 and set up with at least one sling load pendulum motion detecting unit 2 for detecting the pendulum motion 15, 21, 41 of the sling load 12. Additionally, the stabilizer is set up with a working range determination unit S3 for determining the space where free movement is possible in which a rotorcraft 11 with sling load 12 can move without collision and the stabilizer is set up to generate the control signals R in dependency of the determined pendulum motion 15, 31, 41 of the sling load 12 and in dependency of the of the determined working range.

Abstract: A system (1) for the control of at least one unmanned aerial vehicle (2) from at least one aircraft (3), preferably a helicopter. The system (1) comprises at least one computer system (4), at least one satellite communication system (5) online with a satellite (6) and at least one radio set (7) for bidirectional data transfer between the aircraft (3) and the at least one unmanned aerial vehicle (2).