An emergency flotation system for aircraft that, in particular, may be attached to the landing gear or the fuselage of a helicopter, comprising at least two inflatable flotation bodies, each of which are extended in a direction of longitudinal extension and which are spaced apart in a horizontal direction transverse to, in particular, perpendicular to the direction of longitudinal extension, wherein the respective flotation bodies, when inflated, are cross-sectional shaped between their ends that is polygonal perpendicular to their direction of longitudinal extension. An aircraft, in particular, a helicopter, that has an emergency flotation system on its landing gear or fuselage, in particular, wherein the direction of longitudinal extension of the flotation bodies is orientated parallel to the axis of longitudinal extension or transverse, in particular, perpendicular, to the axis of longitudinal extension of the aircraft.
Hold-down and release system (10) for stacked spacecraft (7), configured to change from a hold-down position to a released position with respect to a launcher (13), said system comprising at least one sub-system (20, 20'), each sub-system (20, 20') comprising: - a cable relaxation and rolling assembly configured to be attached to the launcher (13) and comprising: - an inertia drum (2), - an articulated lever (3) configured for engagement and disengagement with the inertia drum (2) at a first end (11) of the articulated lever (3), - an actuator (4) connected to the inertia drum (2) and configured to trigger same, - a cable (5) comprising a first fitting (8), configured to engage with the articulated lever (3) at a second end (12) of the articulated lever (3), and having one of its ends connected to the inertia drum (2), such that the cable (5) can be wound on the inertia drum (2), and additionally comprising a second fitting (9) on the second end of the cable (5), and - a release mechanism (6), configured to be attached to one end of the outermost stacked spacecraft (1), and to hold the second fitting (9) placed on the second end of the cable (5) in the hold-down position, wherein in the hold-down position the articulated lever (3) is engaged with the inertia drum (2) and the first fitting (8) of the cable (5), and the cable (5) is tensioned between the first fitting (8) and the second fitting (9) to keep the stacked spacecraft (7) together, and in the release position the articulated lever (3) is disengaged from the inertia drum (2) and the first fitting (8) of the cable (5).
The invention relates to a multi-phase-buck-power-converter. An embodiment of a multi-phase-buck-power-converter (100) comprises: a first sub-circuit (200) that is configured to supply a first reference voltage; and at least two buck-stages (500). Each buck-stage of the at least two buck-stages comprises: a second sub-circuit (300) that is configured to provide an output current, wherein the second sub-circuit (300) comprises a second resistor (320) to which a second reference voltage can be applied as a function of the output current; and a third sub-circuit (400) that is configured to compare the first reference voltage of the first sub-circuit to the second reference voltage of the second sub-circuit (300) and to correct the output current of the second sub-circuit (300) as a function of a difference between the first reference voltage and the second reference voltage. The at least two buck-stages (500) are connected in parallel to each other. The multi-phase-buck-power-converter further comprises a voltage control unit (60) configured to regulate an output voltage of the multi-phase-buck-power-converter (100).
H02M 3/158 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
4.
PANEL, FASTENING CONSTRUCTION, AIRCRAFT AND OPENING DEVICE
The disclosure herein relates to a panel including an electro-permanent magnet integrated in the panel, and an induction coil connected to the electro-permanent magnet to conduct current induced in the induction coil to the electro-permanent magnet such that the electro-permanent magnet can be switched between a magnetic state and a non-magnetic state. The disclosure herein further relates to a fastening construction, to an aircraft and to an opening device.
H01F 7/20 - ElectromagnetsActuators including electromagnets without armatures
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft
A multilayered radar-absorbing element having adaptable properties for microwave absorption for vehicle parts is described. The element includes a core layer having a first layer thickness, an insulating layer having a second layer thickness, and an outer absorption layer having a third layer thickness. The core layer is manufactured from a magnetically absorbent material. The insulating layer is manufactured from a material which is both electrically insulating and magnetically transmissive. The outer absorption layer is manufactured from a material which is both electrically conductive and magnetically transmissive. The insulating layer is arranged between the core layer and the outer absorption layer. Furthermore, a vehicle part having a plurality of such radar-absorbing elements and a method for producing such a vehicle part are described.
09 - Scientific and electric apparatus and instruments
Goods & Services
Computer software for the agent-based 3D analysis simulation
for the simulation and analysis of multidomain
technical-tactical scenarios (land, sea, air, space, cyber)
for military and civil security applications; computer
software for modelling and simulation of technical platforms
(such as vehicles, aircrafts, ships) with its sensors,
communication and interaction capabilities for military and
civil security applications; computer software for
simulation and training and for creating a virtual
environment for use in learning and simulating weapon system
effectiveness, weapon offensive capabilities, and weapon
defensive capabilities; computer software for scenario
simulation for mission planning and operational analysis
purpose in military and civil security environment.
7.
COATING MATERIAL FOR A SURFACE OF AN AIRCRAFT WITH LIGHTNING PROTECTION
A coating material for a surface of an aircraft includes a polymer-based or rubber-based dielectric matrix material, and first flakes of a metallic and/or soft-magnetic, electrically conductive material that are embedded into the matrix material, wherein the first flakes are geometrically two-dimensional and have a ratio of thickness to average diameter of 1:3 or less, and wherein the first flakes are separated from one another in the matrix material and/or have an electrically non-conductive coating.
m00; transmitting, by a first transceiver coupled to the first processor, the modulated first signal and the modulated second signal; receiving, by a second transceiver, the transmitted first and second signals, wherein the second transceiver is couplable to a second processor configured to process the received first and second signals; and converting, by the second processor, a first baseband of the modulated first carrier frequency to a central baseband carrier frequency, and a second baseband of the modulated second carrier frequency to the central baseband carrier frequency, wherein the conversion to the central baseband carrier frequency is configured to be applied for each hop applied to the modulated first and second carrier frequencies.
A rotary-wing aircraft, comprising: an airframe with an airframe skin that forms an outer airframe loft line and encloses an airframe inner volume, wherein the airframe skin comprises at least one airframe opening; and at least one attachment interface that is mounted to the airframe skin at the airframe opening and configured for a releasable attachment of an external device, wherein the at least one attachment interface comprises an interface cap with a mounting flange that is rigidly attached to the airframe skin, wherein the interface cap comprises at least one pocket that forms a pocket base; and a ball stud with a stud shaft and a ball, wherein the ball stud is rigidly attached to the pocket base and extends at least partly into the airframe opening.
F16M 11/14 - Means for attachment of apparatusMeans allowing adjustment of the apparatus relatively to the stand allowing pivoting in more than one direction with ball-joint
10.
METHOD FOR CONTROLLING GUIDED MISSILES, AND GUIDED MISSILE, AND AIRCRAFT
A method for controlling at least one guided missile to be launched by an aircraft during flight, a guided missile and an aircraft, wherein at least one mission command is transmitted by light signal from the aircraft to the guided missile. The light signal may be transmitted to a transceiver temporarily connected to or integrated into the guided missile.
A rotorcraft with at least one main rotor and at least one engine for powering the at least one main rotor in a normal flight mode, comprising an autorotation training mode control system that is activatable for switching rotorcraft operation between the normal flight mode and an autorotation training mode configured to enable training of autorotation, wherein the autorotation training mode control system comprises at least one main control element that is manually operable for activating the autorotation training mode control system and switching the rotorcraft operation from the normal flight mode to the autorotation training mode to engage the autorotation training mode.
A method for determining the position of a spacecraft in space includes receiving image data from a plurality of differently oriented optics modules, processing the received image data and computing a position, a rate of rotation and/or direction of rotation from the processed image data. The method may be carried out with the aid of at least one image processing module, a device for carrying out such a method, and a computer program for carrying out such a method on such a device.
A photonic transceiver module and a photonic periphery device with a photonic transceiver module for a photonic communication system of an apparatus, as well as the photonic communication system and the apparatus, in particular a vehicle, such as an aircraft, are provided. The photonic transceiver module includes at least one signal interface for receiving and/or transmitting a signal from and/or to, respectively, at least one data collecting and/or transmitting unit for collecting and/or transmitting, respectively, at least one parameter value, an optical modulation unit for translating the signal to and/or from, respectively, the optical domain, and a device adaptor configured to attach the photonic transceiver module to the at least one data collecting and/or transmitting unit to communicate in the optical domain as a node of the photonic communication system.
VISION-BASED SYSTEM AND METHOD FOR THE RELATIVE POSITIONING OF AN OBJECT WITH RESPECT TO A TARGET SURFACE AND A NAVIGATION SYSTEM FOR NAVIGATING SAID OBJECT
The present invention relates to a vision-based system and method for relative positioning with respect to a target surface, characterised in that it comprises: at least three reference markers (1) located on the target surface on the vertices of an equilateral triangle (2) seen from an overhead view of said target surface; at least one image forming device located on the object; processing means configured to receive and process the captured images (4) and configured to either detect the reference markers (1) in the received image (4), or identify the centroid (5) of a triangle (7) formed by the reference markers (1) in the received image (4), or circumscribe the reference markers (1) by means of a circumscribed ellipse (6), or determine the relative position with respect to the target surface by means of the relationship between the circumscribed ellipse (6) and the position of the reference markers (1).
G05D 1/249 - Arrangements for determining position or orientation using signals provided by artificial sources external to the vehicle, e.g. navigation beacons from positioning sensors located off-board the vehicle, e.g. from cameras
G06T 7/73 - Determining position or orientation of objects or cameras using feature-based methods
A kinematic device designed for suspending a load consists of a base element with a base mounting unit, and a top element with a top mounting unit. Connecting these elements is a spring component, which attaches at its base end to the base mounting unit and at its top end to the top mounting unit. The spring generates tension along a motion axis parallel to the base and top elements. Additionally, the device includes a force application component comprising a tensioning element and a force transmission element. The force transmission element connects to the top element and applies a tensile force in the opposite direction to the spring tension force. Also disclosed is a system comprising a plurality of kinematic devices that allows precise control of a top plate's position relative to a base plate.
Matrix cells are used for regeneration in an electrolyzer system. The electrolyte is electrolyzed in the matrix cell. Gas (predominantly product gas) which has unwantedly accessed the electrolyte space is transported off from the electrolyte space into the gas space envisioned therefor by a degassing device. Additional measures such as ultrasonic transducers and field electrodes may realize electrolyte flow and improved transporting-off of gas. A pump may be used to move the electrolyte, and the pump may move the electrolyte by generating bubbles.
B01D 53/22 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by diffusion
C25B 1/04 - Hydrogen or oxygen by electrolysis of water
C25B 9/21 - Cells comprising dimensionally-stable non-movable electrodesAssemblies of constructional parts thereof with diaphragms two or more diaphragms
C25B 9/23 - Cells comprising dimensionally-stable non-movable electrodesAssemblies of constructional parts thereof with diaphragms comprising ion-exchange membranes in or on which electrode material is embedded
The invention relates to an over-voltage-protection-circuit (100) that is configured to protect a high-speed digital signal driver (200) against a positive and negative over voltage injection from an application hardware (210). An embodiment of an over-voltage-protection-circuit (100) comprises: a first semiconductor switch (400) that is configured to short a fault current (231) in the event of an over voltage injection; and an input-circuit-element (300) that is configured to reduce the fault current (231) in the event of an over voltage injection; and a power supply (430) that is connected to a control input of the first semiconductor switch and that is configured to switch the first semiconductor switch (400) in the event of an over voltage injection and to be inactive in a normal operating mode.
H03K 17/06 - Modifications for ensuring a fully conducting state
H03K 17/0812 - Modifications for protecting switching circuit against overcurrent or overvoltage without feedback from the output circuit to the control circuit by measures taken in the control circuit
H03K 17/08 - Modifications for protecting switching circuit against overcurrent or overvoltage
The invention specifies an adjustment aid (10) for orienting an element relative to and on a surface, having a body (12), wherein the body (12) has a passage (14) with an inlet opening (16) and an outlet opening (18), wherein an element can be guided through the passage (14), three indicators (20), wherein the three indicators (20) each have a signal transmitter (22) and a contact point (24), and wherein the connection vectors of the contact points (24) are coplanar, wherein the three indicators (20) are each connected to the body (12) in such a way that they can be brought into contact with a surface via the respective contact points (24), wherein the three indicators (20) are configured such that, when the respective contact points (24) are in contact with the surface, a signal can be generated via the respective signal transmitters ().
B23Q 3/18 - Devices holding, supporting, or positioning, work or tools, of a kind normally removable from the machine for positioning only
B25H 1/00 - Work benchesPortable stands or supports for positioning portable tools or work to be operated on thereby
G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
19.
SEAT BEAM FOR A ROTARY-WING AIRCRAFT ADAPTED FOR RECEIVING SEAT POSTS OF A SEAT BENCH DEVICE
A seat beam for a rotary-wing aircraft adapted for receiving seat posts of a seat bench device, including a first seat beam end; a second seat beam end; and a seat beam body connecting both. A link with a link working line is arranged at the first seat beam end and includes: a link-beam fixation that is attached to the seat beam body and rotatable around a first link rotational axis that is perpendicular to the seat beam extension axis, and a first seat beam fixation that is connected to the link-beam fixation and adapted for being attached to the airframe attachment point such that the first seat beam fixation is rotatable around a second link rotational axis that is parallel to the first link rotational axis.
The present invention belongs to the field of air to air refuelling for aircraft, in particular to the field of systems for generating electrical power at the end of the hose. More particular, the invention provides a system for an air to air refuelling operation which intends to take advantage of the airflow action at the end of the hose in a refuelling operation for generating electrical power needed to supply devices located at the end of the hose.
An aircraft structure having a fuselage, an engine and an air inlet for receiving air for the engine. The air inlet has a cowl which surrounds an inlet opening. The air inlet has a compression surface and a transition shoulder. The air inlet additionally has a flow guide surface, which is arranged as a local elevation in a region of the transition shoulder and extends into the inlet opening. This flow guide surface designed as a local elevation contributes to improving the displacement of the boundary layer of a fluid flowing along the aircraft structure at the air inlet.
A system for thermal regulation of a spacecraft is disclosed including a radiator having a thermally conductive body including at least one radiative surface, at least one diphasic duct extending along the body and in thermal contact with the body. The system includes at least one single-phase cooling fluid circuit and a heat exchange device assembled to the body, the heat exchange device includes a casing having at least an internal cavity having input and output ports for connection with said single-phase cooling fluid circuit, and in that the casing further integrates a first section of each diphasic duct, each section being in thermal contact with the internal cavity.
A deployable reflector is configured to transition from a stowed position to a deployed position, passing through various intermediate positions characterized by peaks and valleys, achieving a paraboloid shape when fully deployed. The reflector includes a central polygonal section, which takes the form of an n-sided polygon, and is supported by a set of 2n radial sections. These radial parts extend from the central polygon and widen towards the outer edge. The radial sections are connected by folds that originate from the vertices of the central polygon and extend outward. These folds are arranged so that in the intermediate positions, the valleys alternate with peaks. When the reflector is in its deployed position, the radial sections form a quadratic surface. On the non-reflective side of the radial folds, there are backing elements made from a material that is more elastic than that of the radial parts.
A structural arrangement for an elongated nose region of a rotary-wing aircraft, including a nose structure that comprises an outer shell with a first shell section and a second shell section arranged diametrically opposed thereto; a first frame; a second frame that is longitudinally spaced apart from the first frame; at least two longitudinal beams which extend on the second shell section between the first frame and the second frame; at least one nose structure floor supported by the at least two longitudinal beams inside of the nose structure; and a center wall that is arranged between the nose structure floor 360 and the first shell section and that extends from the first frame to the second frame.
Disclosed is a method of exchanging cryptographic parameters in a network of tire monitoring devices, the method including broadcasting, from each tire monitoring device to a plurality of other tire monitoring devices, a message comprising a cryptographic parameter generated by that respective tire monitoring device.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Avionic equipment, namely radios and communication hardware for aircraft, unmanned air vehicles and ground stations; Command and control systems for aircraft and unmanned air vehicles, comprised of computer hardware, networking hardware, and recorded software to plan, manage, execute, and train for tactical missions and payload handling; Datalinks being downsized, portable, passive, active or remote electronic devices for receiving, transmitting, reproduction and processing of data, for aircraft and unmanned air vehicles; Computer software providing multi source data fusion, data management, and analysis, to enable military commanders to perform air battle management; Passive and active avionic sensors for situational awareness and target detection. Aircraft; Unmanned air vehicles.
27.
DETERMINISTIC TIME MANAGEMENT AND TIME MANAGEMENT UNIT FOR MULTI-CORE PROCESSORS
A method and system for deterministically managing execution of applications by a multi-core processor on shared resources. The system includes a time management unit, TMU, for controlling execution of at least one application of the applications, a control and/or message bus for transmitting messages between the TMU and each of a multiplicity of cores of the multi-core processor, connection and/or arbitration logic for connecting the multiplicity of cores of the multi-core processor to shared resources based on an action by the TMU to control execution of the at least one application, wherein the TMU is configured to receive a checkpoint reached message from the at least one application, and the checkpoint reached message is sent by the at least one application. The method and system enable the control and deterministic execution of applications of high integrity levels.
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus and instruments for recording, transmitting,
reproducing or processing sound, images or data; navigation,
guidance, tracking, targeting and map making equipment;
optical devices and equipment, enhancers and correctors;
optronic target acquisition system consisting of optical
electronic components for target acquisition devices;
optical electronic components for military reconnaissance
system devices; sensors, detectors and electronic monitoring
instruments and apparatus for military applications; lasers;
laser targeting devices; laser warning apparatus, thermal
imaging equipment, night vision apparatus and day vision
apparatus, systems consisting of the aforesaid goods; day
and night vision cameras; night vision goggles;
electro-optical imaging apparatus and systems in the near
infrared [NIR] and short-wave infrared [SWIR] region;
apparatus and instruments for optical distance and speed
measurement and remote measurement of atmospheric
parameters; sensor systems consisting of a daylight camera
and thermal imaging apparatus; optical and/or electronic
vision systems for vehicles; optical instruments and
amplifiers and parts therefor; optical viewing devices;
residual light image amplifiers; day and night visors and
attachments; targeting apparatus; software for target
recognition; optical apparatus and instruments; recorded
media; computer software; artificial intelligence software
for creating military situation reports; software for
monitoring, analysing, controlling and running physical
world operations; software for virtual and augmented
reality; data processing devices and equipment and
accessories (electrical and mechanical); computers; computer
peripheral devices; hardware and software for transmitting
information to combat operations and surveillance systems;
hardware and software for navigation, guidance, tracking and
targeting optimisation; hardware and software for
environmental monitoring and target detection; software for
sensors, detectors and monitoring instruments and apparatus
for military applications; hardware and software for the
collection, evaluation and systemisation of data and
information; optimisation software; software for monitoring,
analysing, controlling and running physical world
operations; replacement parts and accessories and software
and firmware for all the aforesaid goods; batteries; the
aforesaid goods solely for use in connection with or as part
of optical and/or electronic vision systems and/or equipment
integrated into military platforms. Installation, repair and maintenance of the following goods:
apparatus and instruments for recording, transmitting,
reproducing or processing sound, images or data, navigation,
guidance, tracking, targeting and map making equipment,
optical devices and equipment, enhancers and correctors,
optronic target acquisition system consisting of optical
electronic components for target acquisition devices,
optical electronic components for military reconnaissance
system devices, sensors, detectors and electronic monitoring
instruments and apparatus for military applications, lasers,
laser targeting devices, laser warning apparatus, thermal
imaging equipment, night vision apparatus and day vision
apparatus, systems consisting of the aforesaid goods, day
and night vision cameras, night vision goggles,
electro-optical imaging apparatus and systems in the near
infrared [NIR] and short-wave infrared [SWIR] region,
apparatus and instruments for optical distance and speed
measurement and remote measurement of atmospheric
parameters, sensor systems consisting of a daylight camera
and thermal imaging apparatus, optical and/or electronic
vision systems for vehicles, optical instruments and
amplifiers and parts therefor, optical viewing devices,
residual light image amplifiers, day and night visors and
attachments, targeting apparatus, software for target
recognition, optical apparatus and instruments, recorded
media, computer software, artificial intelligence software
for creating military situation reports, software for
monitoring, analysing, controlling and running physical
world operations, software for virtual and augmented
reality, data processing devices and equipment and
accessories (electrical and mechanical), computers, computer
peripheral devices, hardware and software for transmitting
information to combat operations and surveillance systems,
hardware and software for navigation, guidance, tracking and
targeting optimisation, hardware and software for
environmental monitoring and target detection, software for
sensors, detectors and monitoring instruments and apparatus
for military applications, hardware and software for the
collection, evaluation and systemisation of data and
information, optimisation software, software for monitoring,
analysing, controlling and running physical world
operations, replacement parts and accessories and software
and firmware for all the aforesaid goods, batteries, the
aforesaid goods solely for use in connection with or as part
of optical and/or electronic vision systems and/or equipment
integrated into military platforms; adjustment,
commissioning and service for the repair of electro-optical
devices; repair of electro-optical devices and systems;
installation and maintenance of vehicles and systems for
electronic warfare; installation, cleaning, repair and
maintenance services for electronic warfare equipment;
consultancy and information relating to all the
aforementioned services, included in this class. Scientific and technological services and research and
design services relating thereto; industrial analysis and
research services; design and development of computer
hardware and computer software; scientific and technological
services and scientific and technical consultancy relating
to the following goods: apparatus and instruments for
recording, transmitting, reproducing or processing sound,
images or data, navigation, guidance, tracking, targeting
and map making equipment, optical devices and equipment,
enhancers and correctors, optronic target acquisition system
consisting of optical electronic components for target
acquisition devices, optical electronic components for
military reconnaissance system devices, sensors, detectors
and electronic monitoring instruments and apparatus for
military applications, lasers, laser targeting devices,
laser warning apparatus, thermal imaging equipment, night
vision apparatus and day vision apparatus, systems
consisting of the aforesaid goods, day and night vision
cameras, night vision goggles, electro-optical imaging
apparatus and systems in the near infrared [NIR] and
short-wave infrared [SWIR] region, apparatus and instruments
for optical distance and speed measurement and remote
measurement of atmospheric parameters, sensor systems
consisting of a daylight camera and thermal imaging
apparatus, optical and/or electronic vision systems for
vehicles, optical instruments and amplifiers and parts
therefor, optical viewing devices, residual light image
amplifiers, day and night visors and attachments, targeting
apparatus, software for target recognition, optical
apparatus and instruments, recorded media, computer
software, artificial intelligence software for creating
military situation reports, software for monitoring,
analysing, controlling and running physical world
operations, software for virtual and augmented reality, data
processing devices and equipment and accessories (electrical
and mechanical), computers, computer peripheral devices,
hardware and software for transmitting information to combat
operations and surveillance systems, hardware and software
for navigation, guidance, tracking and targeting
optimisation, hardware and software for environmental
monitoring and target detection, software for sensors,
detectors and monitoring instruments and apparatus for
military applications, hardware and software for the
collection, evaluation and systemisation of data and
information, optimisation software, software for monitoring,
analysing, controlling and running physical world
operations, replacement parts and accessories and software
and firmware for all the aforesaid goods, batteries, the
aforesaid goods solely for use in connection with or as part
of optical and/or electronic vision systems and/or equipment
integrated into military platforms.
29.
Polarization Modulator With Separate Optical Sections
A modulator unit includes a light source, a phase modulator, a polarization component separator, and a reflector. The light source emits an optical signal with two polarization components with their respective polarization direction to the polarization component separator. The polarization component separator sends the polarization components via different optical sections that have different signal propagation times, whereby the polarization components have a relative time offset. The phase modulator modulates a phase of the first polarization component in the first polarization direction and transfers it to the reflector. The reflector retroreflects both polarization components and changes their respective polarization in the process. The polarization components run through the phase modulator again. The phase modulator modulates a phase of the second polarization component in the first polarization direction. The polarization component separator eliminates the time offset between the polarization components. The modulator unit outputs the modulated optical signal as polarization-modulated output signal.
G02F 1/01 - Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulatingNon-linear optics for the control of the intensity, phase, polarisation or colour
An electrically powered multirotor aircraft that is adapted for vertical take-off and landing, comprising a fuselage, at least one aircraft lifting surface that is connected to the fuselage, at least one propeller that is connected to the at least one aircraft lifting surface, a sensor unit, a flutter reduction unit, and a settings adjustment device. The sensor unit is configured to generate sensor data that is indicative of flutter of the at least one aircraft lifting surface. The flutter reduction unit is configured to receive the sensor data to generate flutter reduction signals. The settings adjustment device is configured to receive the flutter reduction signals and to adjust current settings of the at least one propeller based on the flutter reduction signals to reduce flutter of the at least one aircraft lifting surface.
A lightning arrester for a low observable vehicle, in particular stealth aircraft, is proposed, comprising a support structure composed of a first metal alloy having high thermal stability and comprising a diverting structure composed of a second metal alloy having high electrical conductivity, the diverting structure being accommodated at least sectionally in the support structure; and a vehicle, in particular stealth aircraft, comprising at least one such lightning arrester is also proposed.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Electronic instruments for planning aeronautical missions; Computer hardware for planning aeronautical missions; Computer software for planning aeronautical missions; Computer networks for planning aeronautical missions. Design and development of computer software for planning aeronautical missions for others.
33.
MEASUREMENT APPARATUS FOR DETERMINING A BENDING MOMENT
A measurement apparatus for determining a bending moment acting on a rotor shaft of a rotary-wing aircraft as well as to a method of operating such a measurement apparatus. The measurement apparatus includes a processing system and a sensor arrangement that is mounted to a rotor blade which is attached to the rotor shaft. The sensor arrangement includes a sensor that generates a signal in response to a force or moment acting on the rotor blade. A cable transmits the signal from the sensor to the processing system, and the processing system determines the bending moment acting on the rotor shaft based on the signal from the sensor.
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G01D 5/353 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific, research, navigation, surveying, photographic, cinematographic, audiovisual, optical, weighing, measuring, signalling, detecting, testing, inspecting, life-saving and teaching apparatus and instruments; Navigation, guidance, tracking, targeting and map making equipment; Measuring, detecting, monitoring and controlling equipment; Electronic apparatus and control apparatus for use relating to missile defence systems, consisting of a central computing unit, computer software and computer hardware, imaging sensors, in particular infrared sensors, for detecting and locating missiles; Electronic apparatus and control apparatus for use relating to laser defence systems consisting of a central computing unit, computer software and computer hardware, optoelectronic sensors, for detecting and laser beams; Radar detector defence systems; Sensors, communications systems, data processing apparatus and software for data analysis for military targeting and reconnaissance; Apparatus for estimating the situation and situational awareness for aviation; Airspace surveillance systems; Sensors, detectors and monitoring instruments; Opto-electronic detectors; Opto-electronic convertors; Optical sensors; Image intensifiers; Electronic amplifiers; Optical cables; Apparatus for infrared detection and tracking; Optical devices, enhancers and correctors; Opto -electronic devices; Opto-electronic receivers; Opto-electronic jammers; Lasers; Apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data; Video signal processors; Electrical power supplies; Data processing equipment and accessories (electrical and mechanical); Safety, security, protection and signalling devices; Missile warning systems; Warning system for approaching missiles; Alarm and warning apparatus; Radar detectors; Laser warning systems; receivers for radar installations or for radar detectors or for other warning devices; Protective and safety equipment; Computer software; Software for monitoring, analysing, controlling and running physical world operations; Virtual and augmented reality software; Computers on board aircraft; Mission computers. Installation, maintenance and repair of the following goods: Electronic apparatus and control apparatus for use relating to missile defence systems and laser defence systems, radar detector defence systems and airspace surveillance systems. Scientific and technological services and research and design relating thereto; Industrial analysis; Industrial research; Design and development of computer hardware and software; Design and development of the following goods: Computer hardware and computer software for electronic devices for simulating and analysing radar equipment and in particular radar warning systems; Design and development of the following goods: Radar warning systems, including application-specific computer software, computer hardware and communications equipment for radar warning systems; Science and technology services, Scientific and technical consultancy, The aforesaid services relating to missile defence systems, laser defence systems, radar detector defence systems and airspace surveillance systems.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Electric sensors; datalinks being downsized, portable,
passive, active or remote electronic devices for receiving,
transmitting, reproduction and processing of data, ground
control terminals being data processing apparatus and
instruments; all the aforesaid goods being components for
unmanned air vehicles (UAVs); training simulators, namely,
one system integrating software interface and hardware
components to simulate driving and control of unmanned
aerial vehicles. Unmanned air vehicles, namely, drones; unmanned air vehicles
for surveillance, reconnaissance, and weapon delivery.
36.
Reactor Device for Converting Powdered Metal Oxides and Conversion System Comprising Same
Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. (Germany)
Inventor
Seidel, Achim O.
Pal, Uday B.
Pöhle, Georg
Redlich, Christian
Abstract
The present disclosure relates to a reactor device (2) for converting powdered metal oxides, in particular metal oxides contained in regolith, to metal powder and molecular oxygen (O2), the reactor device (2) comprising a cathode reactor vessel (8) providing a receiving space (14) for the powdered metal oxides and adapted to be connected to an electron source (21) such that the powdered electrode oxides can be converted to the metal powder and oxygen ions (O2−) by the application of an electrical potential, and an anode reactor vessel (4) adapted to be connected to an electron sink (22) to attract the oxygen ions (O2−) travelling through an electrolyte (6) from the cathode reactor vessel (8) to the anode reactor vessel (4) during operation of the reactor device (2); wherein the anode reactor vessel (4) at least partially surrounds the cathode reactor vessel (8). Furthermore, the present disclosure relates to a conversion system (1) for converting powdered metal oxides, in particular metal oxides contained in regolith, to a metal powder and molecular oxygen (O2), the conversion system (1) comprising at least one corresponding reactor device (2).
B01J 19/08 - Processes employing the direct application of electric or wave energy, or particle radiationApparatus therefor
B01J 19/00 - Chemical, physical or physico-chemical processes in generalTheir relevant apparatus
B01J 19/24 - Stationary reactors without moving elements inside
B22F 9/14 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes using electric discharge
37.
AIR DIRECTING ARRANGEMENT FOR CONTROLLING AIRFLOW AT AN OUTLET
An air directing arrangement for controlling flow of air at a compartment outlet of a fuselage of a rotorcraft. The air directing arrangement comprises a continuous surface that covers the compartment outlet outside the fuselage and forms a flow channel for directing an air flow at the compartment outlet; a first flow-through opening that is formed at a first position of the flow channel, wherein the first flow-through opening forms an air inlet area; and a second flow-through opening that is formed at a second position of the flow channel, wherein the second flow-through opening is arranged downstream of the first flow-through opening in the predetermined flow direction, and wherein the second flow-through opening forms an air outlet area; wherein the air inlet area is smaller than the air outlet area.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Computer software; communication and networking software,
software; software for data and file management and
databases; software for monitoring, analysing, controlling
and running physical world operations; system and system
support software, and firmware; interface software;
interfaces [interface devices or programmes for computers];
signal cables for IT, AV and telecommunication; software
algorithms for running and connecting video paths;
computers; navigation, guidance, tracking, targeting and map
making devices; sensors, detectors and monitoring
instruments and apparatus; object detectors, movement
detectors. Software development, programming and implementation;
science and technology services and science and technology
consultancy relating to the following goods: computer
software, communication and networking software, software,
software for data and file management and databases,
software for monitoring, analysing, controlling and running
physical world operations, system and system support
software, and firmware, interface software, interfaces
[interface devices or programmes for computers], signal
cables for IT, AV and telecommunication, software algorithms
for running and connecting video paths, computers,
navigation, guidance, tracking, targeting and map making
devices, sensors, detectors and monitoring instruments and
apparatus, object detectors, movement detectors.
39.
GROUND SERVICE DEVICE FOR SECURING ROTOR BLADES OF A ROTARY-WING AIRCRAFT
A ground service system that includes a ground service device and a connecting interface. The ground service device secures rotor blades of a multi-blade rotor of a rotary-wing aircraft in a non-operational mode of the rotary-wing aircraft, when the ground service device is attached to the connecting interface on the rotary-wing aircraft. The ground service device includes a rack with three struts and an attachment device that are releasably attachable to four receiver mounts of the connecting interface. The ground service device further includes clamps for releasably connecting the rotor blades with the four receiver mounts to secure the rotor blades in the non-operational mode of the rotary-wing aircraft.
09 - Scientific and electric apparatus and instruments
Goods & Services
Computer software for the agent-based 3D analysis simulation for the simulation and analysis of multidomain technical-tactical scenarios (Land, Sea, Air, Space, Cyber) for military and civil security applications; Computer software for modelling and simulation of technical platforms (such as vehicles, aircrafts, ships) with its sensors, communication and interaction capabilities for military and civil security applications; Computer software for simulation and training and for creating a virtual environment for use in learning and simulating weapon system effectiveness, weapon offensive capabilities, and weapon defensive capabilities; Computer software for scenario simulation for mission planning and operational analysis purpose in military and civil security environment.
09 - Scientific and electric apparatus and instruments
Goods & Services
Computer software for multi-domain defense simulation, operational analysis, and strategic planning; software for battlefield simulation and wargaming, enabling mission planning, scenario analysis, and resource optimization across air, land, sea, space, and cyber operations; computer software for generating synthetic training data and environments, supporting machine learning model development, testing, and validation for defense applications; software for creating virtual environments and Computer Generated Forces (CGF) for simulation, training, and testing of weapon systems, multi-domain strategies, and command post exercises; computer software for simulation of multi-domain military operations, including urban terrain, maritime environments, and command structures; virtual reality software for simulating interactions with terrain, vehicles, weapons, and adversarial forces across domains in a virtual environment for military training and experimentation; computer software for scenario simulation, enabling virtual training for multi-domain tactics, operational decision-making, and system-of-systems analysis in defense contexts.
A ball lock pin comprising a pin body with an inner accommodation and at least one locking ball accommodation; a blocking pin at least partly arranged in the inner accommodation and movable between a blocking position and a releasing position; at least one locking ball movably arranged in the at least one locking ball accommodation and biased into a locking position by the blocking pin, if the blocking pin is in the blocking position, wherein the at least one locking ball is released for moving into an unlocking position if the blocking pin is in the releasing position; a primary spring element arranged in the inner accommodation and biasing the blocking pin into the blocking position; and a redundant spring element arranged in the inner accommodation and biasing the blocking pin into the blocking position.
The invention relates to an optical apparatus (1) comprising an objective (2) and an optical inversion device (3) which are arranged along a beam path (4) of radiation (5). According to the invention, the inversion device (3) has a front inversion half (6) and at least one rear inversion half (7) spaced apart from the front inversion half (6) along the beam path (4), wherein an air gap (8) is formed between the front inversion half (6) and the rear inversion half (7), into which air gap a beam-splitter device (9) can be introduced such that the radiation (5) can be at least partially coupled out of the beam path (4) into a side beam path (10).
G02B 9/12 - Optical objectives characterised both by the number of the components and their arrangements according to their sign, i.e. + or – having three components only
G02B 13/14 - Optical objectives specially designed for the purposes specified below for use with infrared or ultraviolet radiation
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data; navigation, guidance, tracking, targeting and map making equipment; optical devices and equipment, enhancers and correctors; optronic target acquisition system consisting of optical electronic components for target acquisition devices; optical electronic components for military reconnaissance system devices; sensors, detectors and electronic monitoring instruments and apparatus for military applications; lasers; laser targeting devices; laser warning apparatus, thermal imaging equipment, night vision apparatus and day vision apparatus, systems consisting of the aforesaid goods; day and night vision cameras; night vision goggles; electro-optical imaging apparatus and systems in the near infrared [NIR] and short-wave infrared [SWIR] region; apparatus and instruments for optical distance and speed measurement and remote measurement of atmospheric parameters; sensor systems consisting of a daylight camera and thermal imaging apparatus; optical and/or electronic vision systems for vehicles; optical instruments and amplifiers and parts therefor; optical viewing devices; residual light image amplifiers; day and night visors and attachments; targeting apparatus; software for target recognition; optical apparatus and instruments; recorded media; computer software; artificial intelligence software for creating military situation reports; software for monitoring, analysing, controlling and running physical world operations; software for virtual and augmented reality; data processing devices and equipment and accessories (electrical and mechanical); computers; computer peripheral devices; hardware and software for transmitting information to combat operations and surveillance systems; hardware and software for navigation, guidance, tracking and targeting optimisation; hardware and software for environmental monitoring and target detection; software for sensors, detectors and monitoring instruments and apparatus for military applications; hardware and software for the collection, evaluation and systemisation of data and information; optimisation software; software for monitoring, analysing, controlling and running physical world operations; replacement parts and accessories and software and firmware for all the aforesaid goods; batteries; the aforesaid goods solely for use in connection with or as part of optical and/or electronic vision systems and/or equipment integrated into military platforms. Installation, repair and maintenance of the following goods: apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data, navigation, guidance, tracking, targeting and map making equipment, optical devices and equipment, enhancers and correctors, optronic target acquisition system consisting of optical electronic components for target acquisition devices, optical electronic components for military reconnaissance system devices, sensors, detectors and electronic monitoring instruments and apparatus for military applications, lasers, laser targeting devices, laser warning apparatus, thermal imaging equipment, night vision apparatus and day vision apparatus, systems consisting of the aforesaid goods, day and night vision cameras, night vision goggles, electro-optical imaging apparatus and systems in the near infrared [NIR] and short-wave infrared [SWIR] region, apparatus and instruments for optical distance and speed measurement and remote measurement of atmospheric parameters, sensor systems consisting of a daylight camera and thermal imaging apparatus, optical and/or electronic vision systems for vehicles, optical instruments and amplifiers and parts therefor, optical viewing devices, residual light image amplifiers, day and night visors and attachments, targeting apparatus, software for target recognition, optical apparatus and instruments, recorded media, computer software, artificial intelligence software for creating military situation reports, software for monitoring, analysing, controlling and running physical world operations, software for virtual and augmented reality, data processing devices and equipment and accessories (electrical and mechanical), computers, computer peripheral devices, hardware and software for transmitting information to combat operations and surveillance systems, hardware and software for navigation, guidance, tracking and targeting optimisation, hardware and software for environmental monitoring and target detection, software for sensors, detectors and monitoring instruments and apparatus for military applications, hardware and software for the collection, evaluation and systemisation of data and information, optimisation software, software for monitoring, analysing, controlling and running physical world operations, replacement parts and accessories and software and firmware for all the aforesaid goods, batteries, the aforesaid goods solely for use in connection with or as part of optical and/or electronic vision systems and/or equipment integrated into military platforms; adjustment, commissioning and service for the repair of electro-optical devices; repair of electro-optical devices and systems; installation and maintenance of vehicles and systems for electronic warfare; installation, cleaning, repair and maintenance services for electronic warfare equipment; consultancy and information relating to all the aforementioned services, included in this class. Scientific and technological services and research and design services relating thereto; industrial analysis and research services; design and development of computer hardware and computer software; scientific and technological services and scientific and technical consultancy relating to the following goods: apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data, navigation, guidance, tracking, targeting and map making equipment, optical devices and equipment, enhancers and correctors, optronic target acquisition system consisting of optical electronic components for target acquisition devices, optical electronic components for military reconnaissance system devices, sensors, detectors and electronic monitoring instruments and apparatus for military applications, lasers, laser targeting devices, laser warning apparatus, thermal imaging equipment, night vision apparatus and day vision apparatus, systems consisting of the aforesaid goods, day and night vision cameras, night vision goggles, electro-optical imaging apparatus and systems in the near infrared [NIR] and short-wave infrared [SWIR] region, apparatus and instruments for optical distance and speed measurement and remote measurement of atmospheric parameters, sensor systems consisting of a daylight camera and thermal imaging apparatus, optical and/or electronic vision systems for vehicles, optical instruments and amplifiers and parts therefor, optical viewing devices, residual light image amplifiers, day and night visors and attachments, targeting apparatus, software for target recognition, optical apparatus and instruments, recorded media, computer software, artificial intelligence software for creating military situation reports, software for monitoring, analysing, controlling and running physical world operations, software for virtual and augmented reality, data processing devices and equipment and accessories (electrical and mechanical), computers, computer peripheral devices, hardware and software for transmitting information to combat operations and surveillance systems, hardware and software for navigation, guidance, tracking and targeting optimisation, hardware and software for environmental monitoring and target detection, software for sensors, detectors and monitoring instruments and apparatus for military applications, hardware and software for the collection, evaluation and systemisation of data and information, optimisation software, software for monitoring, analysing, controlling and running physical world operations, replacement parts and accessories and software and firmware for all the aforesaid goods, batteries, the aforesaid goods solely for use in connection with or as part of optical and/or electronic vision systems and/or equipment integrated into military platforms.
45.
AN APPARATUS FOR CONNECTION TO AN ANCHOR TRACK OR AN ANCHOR POINT IN AN AIRCRAFT
An apparatus for connection to an anchor track or an anchor point in an aircraft, comprising a main body, a quick fastening device that is attached to the main body and configured for being removably fastened to the anchor track or the anchor point, and at least a first connecting element and a second connecting element which are attached to the main body and configured for being connected to external load connecting devices.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
28 - Games; toys; sports equipment
37 - Construction and mining; installation and repair services
41 - Education, entertainment, sporting and cultural services
Goods & Services
(1) Computer hardware; computers; flight simulators; simulators for the steering and control of vehicles
(2) Flight control apparatus for the piloting of helicopters and rotorcraft, namely, helicopter and rotorcraft control panels, electromechanical controls for helicopters and rotorcraft, electronic controllers for helicopters and rotorcraft flight control systems; electronic controllers for the piloting of helicopters and rotorcraft; fly-by-wire flight control systems for helicopters and rotorcraft; navigational apparatus and instruments for helicopters and rotorcraft, namely, autonomous navigation systems for helicopters and rotorcraft; helicopters and rotorcraft navigation apparatus in the form of on-board computers; computer software for helicopter and rotorcraft navigation, computer software for helicopter and rotorcraft pilot training; flight simulation games; electronic publications recorded on computer media in the nature of flight manuals; electronic publications, downloadable, in the nature of flight manuals.
(3) Helicopters and rotorcraft. (1) Installation, upgrading, maintenance, repair and overhaul of helicopters and rotorcraft; installation, upgrading, maintenance, repair, overhaul of helicopter and rotorcraft flight simulators.
(2) Training services relating to the piloting, maintenance, repair and overhaul of helicopters and rotorcraft.
47.
METHOD OF DETERMINING A REMAINING OPERATING TIME OF AN ELECTRICAL ENERGY STORAGE UNIT IN AN AIRCRAFT
A method of determining a remaining operating time of an electrical energy storage unit in an aircraft, comprising: using a first sensor arrangement for measuring first performance parameters of the electrical energy storage unit; determining first performance indicators based on the first performance parameters; using at least one second sensor arrangement for measuring second performance parameters of the electrical energy storage unit; determining second performance indicators based on the second performance parameters; comparing the first performance indicators with the second performance indicators to determine consolidated performance indicators; and determining predictive remaining operating times of the electrical energy storage unit based on the consolidated performance indicators, wherein the predictive remaining operating times comprise at least a predictive nominal remaining operating time and a predictive emergency remaining operating time.
G01R 31/3842 - Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
G01R 31/374 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC] with means for correcting the measurement for temperature or ageing
48.
Active antenna especially for the space-technology field
An active antenna is disclosed including a passive portion of an antenna array extended at one end by a plate in which apertures are formed, at least one active assembly for transmitting radiofrequency RF waves, called assembly, through said apertures, each assembly including a first row of active modules facing apertures of the plate, a second row of active modules facing apertures of the plate and attached to the first row of active modules, a beam attached to the plate and held clamped between the first and second rows of active modules, a heat-transfer duct in contact with the first and second rows of active modules and jutting out on either side of said first and second rows of active modules.
H01Q 1/02 - Arrangements for de-icingArrangements for drying-out
H01Q 3/12 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
An arrangement for actuating a closure element that is movable to selectively close and open up an outlet opening of a tank, which can be received or is accommodated in an aircraft, of a device for dropping water for firefighting. The arrangement is formed with a Geneva drive mechanism and makes it possible for the closure element situated in an opened position to be closed to close the outlet opening in a closed position, for the closure element to be locked in the closed position, and for the closure element locked in the closed position to be unlocked for opening the closure element, when the tank is full, to release water. A device with the arrangement for dropping water from an aircraft for firefighting purposes and an aircraft with the device are disclosed.
A mechanical switching unit for selectively moving a functional component from a first position to a second position has an input element, an output element, a first holding point and a second holding point. The input element is set in motion by a drive. The output element is in engagement with the input element and is set in motion by the input element. The input element moves the output element from the first position to the second position, and vice versa. In the process, the functional component is moved from the first position to the second position, and vice versa. The first holding point exerts a first holding force on the functional component in the first position. The second holding point exerts a second holding force on the functional component in the second position.
In general, the present invention relates to a configurable light signal. More particularly, the present invention relates to an apparatus for providing a configurable light signal, to a moving object comprising such an apparatus and to a method for providing a configurable light signal. An embodiment of the apparatus comprises at least one light source 110, a spatial light modulator 120, a lens system 130, and a controller device 122. The at least one light source 110, the spatial light modulator 120 and the lens system 130 are configured and arranged to provide a light trajectory beginning from the at least one light source 110 to the spatial light modulator 120 into the lens system 130 and out of the lens system 130 to a search field 140. The controller device 122 is configured to control the spatial light modulator 120 and the spatial light modulator 120 is configured to modulate the light of the light trajectory spatially to provide at least one contour limited footprint 141 of the light within the search field 140.
A method for operating a synthetic aperture radar, SAR, mode, in an SAR instrument, wherein the method comprises the steps of: acquiring at least one subswath positioned in an across track direction of a movement of the SAR instrument, wherein the at least one subswath is acquired during at least one acquisition burst duration and/or at a predetermined radio frequency bandwidth; adjusting the at least one acquisition burst duration and/or the predetermined radio frequency bandwidth and/or a number of parallel simultaneous subswaths and/or an inserted burst duration for a further subswath based upon a predetermined parameter; constructing an SAR image based on the acquired at least one subswath.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Computer software; communication and networking software, software; software for data and file management and databases; software for monitoring, analysing, controlling and running physical world operations; system and system support software, and firmware; interface software; interfaces [interface devices or programmes for computers]; signal cables for IT, AV and telecommunication; software algorithms for running and connecting video paths; computers; navigation, guidance, tracking, targeting and map making devices; sensors, detectors and monitoring instruments and apparatus; object detectors, movement detectors. Software development, programming and implementation; science and technology services and science and technology consultancy relating to the following goods: computer software, communication and networking software, software, software for data and file management and databases, software for monitoring, analysing, controlling and running physical world operations, system and system support software, and firmware, interface software, interfaces [interface devices or programmes for computers], signal cables for IT, AV and telecommunication, software algorithms for running and connecting video paths, computers, navigation, guidance, tracking, targeting and map making devices, sensors, detectors and monitoring instruments and apparatus, object detectors, movement detectors.
54.
GUIDANCE SYSTEM AND METHOD OF AN ELEMENT TOWARDS A TARGET
Guidance system and method of an element (1) towards a target (2). The guidance system comprising: - at least one imaging device to view the target (2) and the element (1), - a control means in communication with the imaging device and with the element (1) that receives the images taken by the imaging device, the control means configured to: - locate in the images a reference mark of the element (1) and of the target (2), - send an instruction to move the element (1) so that the reference mark of the element (1) is located in a predetermined position with respect to the target (2) in the received images, - while the element (1) is controlled to keep the predetermined position, send an instruction to move the element (1) towards the target (2), and - continuously perform the above steps until the element (1) reaches the target (2).
G05D 1/243 - Means capturing signals occurring naturally from the environment, e.g. ambient optical, acoustic, gravitational or magnetic signals
G05D 1/672 - Positioning of towed, pushed or suspended implements, e.g. ploughs
G05D 1/697 - Coordinated control of the position or course of two or more vehicles for rendezvous of two or more vehicles, e.g. for in-flight refuelling
G05D 105/22 - Specific applications of the controlled vehicles for transportation of humans
An external cargo adapter for use with a rotorcraft that comprises at least one carrier station, in particular at least one weapon station, comprising: at least one mounting lug for attachment to the at least one carrier station; at least one cargo carrying ring for connection to a connecting rope adapted for transport of an external cargo; and a connecting member that connects the at least one mounting lug with the at least one cargo carrying ring.
B64D 1/08 - Dropping, ejecting, or releasing articles the articles being load-carrying devices
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64D 1/22 - Taking-up articles from earth's surface
56.
Apparatus Management System For Controlling At Least One Function Of An Apparatus
An apparatus management system for controlling at least one function of an apparatus, such as a vehicle, operated by an operator and exposed to a potential impact approaching the apparatus, includes: an impact reaction system, configured for generating a command for controlling the at least one function of the apparatus; wherein the impact reaction system includes: an intervention control unit; and an operator notification unit. The intervention control unit includes at least one control model configured for assessing at least one command for controlling the at least one function of the apparatus to perform an intervention to avoid the impact. The operator notification unit is configured to issue at least one notification to the operator regarding the at least one command. The intervention control unit is configured to output the at least one command for controlling the at least one function of the apparatus subsequent to issuance of the notification.
An assembly with a hinged door pivotally mounted to a carrier element, and a locking system for locking the hinged door in an open position, wherein the locking system comprises a hinge bracket rigidly attached to the carrier element, the hinge bracket comprising a locking notch; and an open-door locking device comprising a mounting bracket pivotally mounted to the hinge bracket; a housing connected to the mounting bracket and rigidly attached to the hinged door; a sliding block slidable in the housing between a normal position and an actuated position; and a slider slidable in the housing between a blocking position and a releasing position, the slider being in the blocking position and engaging the locking notch of the hinge bracket for blocking the hinged door in the open position when the sliding block is in the normal position.
A vehicle management system includes a missile avoidance system that generates command for controlling at least one function of a vehicle. The missile avoidance system includes a maneuver control unit and a missile avoidance management unit. The maneuver control unit includes at least two control models. Each of the at least two control models generates the command for controlling the at least one function of the vehicle, and each of the at least two control models can be selectively put in an active state or an inactive state. The missile avoidance management unit selects one of the at least two control models and putts it in the active state. The maneuver control unit outputs the command for controlling the at least one function of the vehicle provided by the control model that is in the active state.
A primary component (100) for an aircraft (10) comprises a first surface (102) and a second surface (104) arranged opposite the first surface (102) as well as a heat exchanger (200). The heat exchanger (200) comprises a heat exchanger body (201) and a plurality of ports (212, 214, 222, 224). The heat exchanger (200) defines a first fluid circuit (210) and a second fluid circuit (220), wherein each fluid circuit is fluidically connected to two ports, respectively, and the first fluid circuit (210) is fluidically separated from the second fluid circuit (220). The heat exchanger body (201) is embedded in the primary component (100) in such a way that the heat exchanger body (201) is arranged between the first surface (102) and the second surface (104) of the primary component (100), and each of the plurality of ports (212, 214, 222, 224) is fluidically accessible either via the first surface (102) or via the second surface (104).
A multiple hold down and release device for restraining and releasing a payload from a spacecraft performs methods to release a payload from a spacecraft and install a multiple hold down and release device. At a periphery, the device includes hold-down assemblies. Each assembly has a hold-down bracket configured to attach to the payload and a hold-down support, both having conical mating surfaces. Each hold-down support includes a torsion spring(s) around an axis. In pairs of connecting levers, each lever includes a first end coupling to a corresponding hold-down support such that each corresponding lever is articulated with the corresponding hold-down support through an axis; and a second end opposite the first end. Restraint cables join second ends of each pair of connecting levers and are arranged radially with a central area where the restraint cables cross. A central release actuator is configured for cutting the restraint cables.
The invention relates to an unfurlable reflector telescope (2), in particular for a satellite (1), preferably a small/miniaturised satellite or CubeSat, at least comprising: - a folding segmented main reflector (3), formed by a number of separate planar reflector segments (3a) which are connected via first hinge devices (4) to an unfolding support structure (5); - the unfolding support structure (5), which is intended for receiving the reflector elements (3a) of the main reflector (3) and is formed by a plurality of first rod-shaped connection elements (5a) which are interconnected via second hinge devices (5b); and - an unfolding secondary reflector (6).
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
62.
Method, Device and Computer Program for Determining the Position of a Satellite Using a Star Tracker
A method for determining the position of a satellite rotating about an axis of rotation using at least a star tracker which is aligned along an optical axis with a recorded light object field, the axis of rotation and the optical axis being at a fixed angle relative to one another and a light sensor having a sensor surface which is perpendicular to the optical axis and contains a sensor coordinate system having an arrangement of light-sensitive pixels in rows being provided. To achieve improved position control of the satellite, image data recorded in the individual rows of the light sensor are recorded row by row and sequentially, the image data for each row are convoluted with a predefined number of pixels over a predefined time interval using a boxcar operator, a light maximum is identified using the boxcar operator, the light maximum is assigned to a location of a light object on the basis of a position of the row and within the row in the sensor coordinate system, and an object list containing light object coordinates, the light maximum and a measurement time is identified from a plurality of light objects using an over the entire sensor coordinate system.
An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.
A rotorcraft flight training method for a rotorcraft comprising at least two engines and at least one rotor providing lift helping to keep the rotorcraft in the air. The method comprises at least the following steps: flying the rotorcraft in a mode wherein each engine supplies driving power to the rotor; and activating a first command to start a training phase simulating asymmetric flight, the training phase comprising a first flight phase comprising a first control operation, with a controller, controlling the at least two engines and a first display operation for displaying, with a display, information carrying at least two simulated powers.
G09B 9/46 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer the aircraft being a helicopter
A method for joining a window frame to a fuselage skin of an aircraft made of a fiber composite material, includes providing the window frame, making a window opening in the fuselage skin, arranging a curable connecting layer around the window opening, pressing the window frame onto the connecting layer, hardening the composite of fuselage skin, connecting layer and window opening.
A method of operating a rotorcraft with at least one main rotor and at least two engines, comprising: determining whether the rotorcraft is operated in an AEO mode wherein the at least two engines are powering the at least one main rotor, or in a SEO mode wherein only a first engine of the at least two engines is powering the at least one main rotor while a second engine of the at least two engines is inactive; if the rotorcraft is operated in the SEO mode, monitoring the first engine to enable detection of engine failures; and if during monitoring of the first engine an engine failure of the first engine is detected, entering into autorotation of the at least one main rotor upon detection of the engine failure by adjusting main rotor actuators of the at least one main rotor.
A system for information transmission in a quantum communication network is provided. An embodiment of the system comprises: - a first laser signal source configured to generate a first laser signal, and - a second laser signal source configured to generate a second laser signal, wherein each laser signal source is configured to provide the corresponding laser signal to - a coupler unit, wherein said coupler unit is configured to receive and to couple both laser signals, and to provide coupled laser signals to - an optical waveguide, wherein said optical waveguide is configured to - receive the coupled laser signals and - cause a concentric alignment of the coupled laser signals by allowing the received coupled laser signals a mode propagation to provide concentrically aligned laser signals to - a directional unit, wherein said directional unit is configured to receive the concentric aligned laser signals and to provide the concentrically aligned laser signals to a second terminal of the quantum communication network.
A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, the upper primary skin being mounted on top of a predetermined number of supporting beams; wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement such that the firewall arrangement defines a fire proof separation at least between the at least one aircraft engine and the aircraft interior region; and wherein the firewall arrangement comprises at least a funnel-shaped lower firewall arranged between the at least one aircraft engine and the upper primary skin of the fuselage.
A method of processing engine monitoring parameters in a rotorcraft that comprises at least one rotor and at least two engines for powering the at least one rotor in one of an All Engines Operative mode and a Single Engine Operation mode, wherein the engine monitoring parameters are at least indicative of power margins of one engine of the at least two engines of the rotorcraft, wherein the method comprises displaying an engine monitoring indicator for the one engine of the at least two engines of the rotorcraft for visualizing a current performance state of the one engine; and, if the rotorcraft is operated in the Single Engine Operation mode, displaying a first graphical representation of a Single Engine Operation mode indicator with the engine monitoring indicator for visualizing that the rotorcraft is operated in the Single Engine Operation mode.
A detector module for image capture, in particular for an optoelectronic image capture system for an aircraft, such as a spacecraft, comprising a main module body and at least one optoelectronic element arranged on and/or integrated in the main module body, wherein the at least one optoelectronic element has at least one line with a multiplicity of pixels, such as pixel line, and an optoelectronic image capture system and aircraft, such as spacecraft.
H04N 23/52 - Elements optimising image sensor operation, e.g. for electromagnetic interference [EMI] protection or temperature control by heat transfer or cooling elements
B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for
G03B 15/00 - Special procedures for taking photographsApparatus therefor
G03B 30/00 - Camera modules comprising integrated lens units and imaging units, specially adapted for being embedded in other devices, e.g. mobile phones or vehicles
H04N 23/54 - Mounting of pick-up tubes, electronic image sensors, deviation or focusing coils
H04N 23/90 - Arrangement of cameras or camera modules, e.g. multiple cameras in TV studios or sports stadiums
71.
Control device and plasma energy protective apparatus for an ion thruster
A control device for a frequency generator of an ion thruster is described. The control device permits the detection of zero-crossings in a current and/or voltage characteristic during specific time intervals only, which detection is inhibited during other time intervals. Any incorrect switching performance of the control device associated with erroneously detected zero-crossings is prevented accordingly. A low-pass filter filters harmonics out of the detected current and/or voltage characteristics. A time-delay element offsets stray delays in the detection of zero-crossings. Additionally, plasma energy protective apparatuses are described, which attenuate the impact of any power flashover from a thruster unit to a power supply unit of an ion thruster.
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Navigation, guidance, tracking, targeting and map making
devices; measuring, detection and monitoring instruments,
devices and controllers; audio/visual and photographic
devices; enhancers; correctors; sensor systems consisting of
a daylight camera and thermal imaging apparatus; optical
and/or electronic vision systems for vehicles; optical
instruments and enhancers and parts therefor; optical
viewing devices; spotting scopes; thermal imaging apparatus;
apparatus providing night vision; daylight cameras; night
vision goggles; sensors; attachment lenses; objective and
ocular lenses; observation eyepieces; distance measuring
apparatus; laser range finders; laser targeting device;
residual light image intensifier; day and night sights and
attachments; target devices; target recognition devices and
software; optical apparatus; sighting or simulation
apparatus and instruments for shooting purposes; spare parts
and accessories and software and firmware for all of the
aforesaid goods; batteries; the aforesaid goods for use only
in connection with or as part of optical and/or electronic
sighting systems and/or equipment incorporated in military
vehicles; none of the aforementioned goods for use in
connection with the testing, monitoring or detection of
fuels, chemicals and other substances. Installation and maintenance of data processing devices and
computer hardware; consultancy in relation to all of the
aforesaid services; adjustment, commissioning and service
for the repair of electro-optical equipment; maintenance and
repair of electro-optical devices and installations for
third parties; installation and maintenance of electronic
warfare vehicles and equipment and systems; installation,
cleaning, repair and maintenance services for electronic
warfare equipment; consultancy in relation to repair,
maintenance and installation and repair, maintenance and
installation in relation to all of the following goods:
navigation, guidance, tracking, targeting and map making
devices, measuring, detection and monitoring instruments,
devices and controllers, audio/visual and photographic
devices, enhancers, correctors, sensor systems consisting of
a daylight camera and thermal imaging apparatus, optical
and/or electronic vision systems for vehicles, optical
instruments and enhancers and parts therefor, optical
viewing devices, spotting scopes, thermal imaging apparatus,
apparatus providing night vision, daylight cameras, night
vision goggles, sensors, attachment lenses, objective and
ocular lenses, observation eyepieces, distance measuring
apparatus, laser range finders, laser targeting device,
residual light image intensifier, day and night sights and
attachments, target devices, target recognition devices and
software, optical apparatus, sighting or simulation
apparatus and instruments for shooting purposes, spare parts
and accessories and software and firmware for all of the
aforesaid goods, batteries; the aforementioned services only
for use in connection with or as part of optical and/or
electronic sighting systems and/or equipment integrated into
military vehicles; none of the aforementioned services for
use in connection with the testing, monitoring or detection
of fuels, chemicals and other substances. Scientific and technological services and scientific and
technical consultancy relating to all of the following
goods: navigation, guidance, tracking, targeting and map
making devices, measuring, detection and monitoring
instruments, devices and controllers, audio/visual and
photographic devices, enhancers, correctors, sensor systems
consisting of a daylight camera and thermal imaging
apparatus, optical and/or electronic vision systems for
vehicles, optical instruments and enhancers and parts
therefor, optical viewing devices, spotting scopes, thermal
imaging apparatus, apparatus providing night vision,
daylight cameras, night vision goggles, sensors, attachment
lenses, objective and ocular lenses, observation eyepieces,
distance measuring apparatus, laser range finders, laser
targeting device, residual light image intensifier, day and
night sights and attachments, target devices, target
recognition devices and software, optical apparatus,
sighting or simulation apparatus and instruments for
shooting purposes, spare parts and accessories and software
and firmware for all of the aforesaid goods, batteries;
design and development of computer hardware and software for
navigation, guidance, tracking, targeting and map making
devices, measuring, detection and monitoring instruments,
devices and controllers, audio/visual and photographic
devices, enhancers, correctors, sensor systems consisting of
a daylight camera and thermal imaging apparatus, optical
and/or electronic vision systems for vehicles, optical
instruments and enhancers and parts therefor, optical
viewing devices, spotting scopes, thermal imaging apparatus,
apparatus providing night vision, daylight cameras, night
vision goggles, sensors, attachment lenses, objective and
ocular lenses, observation eyepieces, distance measuring
apparatus, laser range finders, laser targeting device,
residual light image intensifier, day and night sights and
attachments, target devices, target recognition devices and
software, optical apparatus, sighting or simulation
apparatus and instruments for shooting purposes, batteries;
the aforementioned services only for use in connection with
or as part of optical and/or electronic sighting systems
and/or equipment integrated into military vehicles; none of
the aforementioned services for use in connection with the
testing, monitoring or detection of fuels, chemicals and
other substances.
73.
PASSIVE POSITION DETERMINATION USING A CORRECTION-BASED TIME DIFFERENCE OF ARRIVAL OF A COLLABORATIVE MULTI-STATIC RADAR
The invention relates to a relative position determination device comprising at least four transceiver units, wherein each of the at least four transceiver units is configured and designed to transmit - a broadband signal having a broadband signal property and - a position signal having information about an inherent and/or relative position of the transceiver unit, in such a way that an object approaching the device can determine its position relative to the device from differences between object-inherent reception times of the broadband signal property of received broadband signals and received position signals.
G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves
G01S 5/10 - Position of receiver fixed by co-ordinating a plurality of position lines defined by path-difference measurements
G01S 5/06 - Position of source determined by co-ordinating a plurality of position lines defined by path-difference measurements
74.
SYSTEM AND METHOD FOR REFUELLING A TANKER AIRCRAFT, COMPRISING A BOOM HOSE ADAPTOR
System and method for refuelling a tanker aircraft (1), comprising a boom hose adaptor (9), the refuelling system comprising: a rigid boom (5), the boom hose adaptor (9) which comprises a hose portion (8) and a coupling end (4), at least a sensor configured to be located in the tanker aircraft (1) and to obtain data relating to the location of the receiver aircraft (3) with respect to the tanker aircraft (1), and a control means configured to be located inside the tanker aircraft (1) and connectable to the sensor to receive the data from the sensor, and to the tanker aircraft (1) to control the position of the rigid boom (5) so as to place the boom hose adaptor (9) within a range of positions according to the data obtained from the sensor.
An amplifier arrangement has a plurality of function strings, which are required for nominal operation. In addition, the amplifier arrangement has a redundancy circuit and a redundant function string including a redundant converter and a redundant amplifier. If a function string is faulty, the redundancy circuit supplies the input signals of the faulty function string to the redundant function string. In addition, a high-frequency system with an inner housing and an outer housing is described, wherein an air gap separates the inner housing and the outer housing from one another so that high-frequency signals can be transmitted via the air gap between the inner housing and the outer housing.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Electric sensors; datalinks being downsized, portable, passive, active or remote electronic devices for receiving, transmitting, reproduction and processing of data, ground control terminals being data processing apparatus and instruments; all the aforesaid goods being components for Unmanned Air Vehicles (UAVs); training simulators, namely, one system integrating software interface and hardware components to simulate driving and control of unmanned aerial vehicles. Unmanned air vehicles, namely, drones; unmanned air vehicles for surveillance, reconnaissance, and weapon delivery; UAV systems composed of UAVs and component parts, containing sensors, downsized, portable, passive and active remote ground control terminals, data links comprised of ground control terminals and airborne data terminals that allow the UAV to be controlled by the ground operators and further allow data to be transmitted from the UAV to the ground operators.
77.
REDUNDANT CONTROL SYSTEM FOR AN AIR TO AIR REFUELLING SYSTEM
The present invention belongs to the technical field of air to air refuelling for aircraft, in particular to the field of systems for controlling the hose tension during contact operation in a hose and drogue refuelling system. More particular, the invention provides a redundant control system for keeping hose in tension during contact operation in a hose and drogue refuelling system and a method for keeping the hose in tension during contact operation in the hose and drogue refuelling system.
System (1) for hold down and release of a spacecraft with respect to a launcher, configured to be able to change from a closed state to an open state, that comprises: - an upper bracket (2) in the form of a ring comprising an inner protruding portion (4), - a lower bracket (3) in the form of a ring comprising an inner protruding portion (4'), - an internal assembly (5) fixed to the lower bracket (3) that comprises a central beam (6), at least three levers (7), at least three clamps (8), at least three guiding systems for the clamps (8), a central rod (11) and an actuator (12), wherein: - the upper bracket (2) and the lower bracket (3) enclose an interior hollow space where the internal assembly (5) is placed in a closed state of the system (1), - the clamps (8) of the internal assembly (5) have a peripheral groove (13) configured to mate with the protruding portions (4, 4') of the upper bracket (2) and the lower bracket (3), - each lever (7) is rigid, is articulated to a clamp (8) by a hinge (14) and to the central beam (6) by a hinge (14') and comprises a latch system (15) to fix the lever (7) on the central beam (6) in an open state of the system (1), - the clamps (8) are guided by the guiding systems that allow the radial movement of the clamps (8), each guiding system comprising a guide (9) on which at least one pin (10) protruding from the corresponding clamp (8) is fitted, and - the central rod (11) is joined to the central beam (6), is preloaded in a closed state of the system (1) by torquing an upper nut (19) and is releasable by the action of the actuator (12).
An air-conducting structure (100) for an aircraft including a first duct portion (110) configured to conduct a first air stream (111), a second duct portion (120) which opens into the first duct portion (110) and is configured to conduct a second air stream (121), and a vaned rotor (130) in the first duct portion (110) and driven by the second air stream (121). The air-conducting structure (100) may be used as or in an air ejector or ejector pump.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
A structurally bonded arrangement comprising: an interconnecting component; a first component with a first connecting area that is rigidly connected to the interconnecting component; and a second component with a second connecting area that is structurally bonded to the interconnecting component in an associated bonding area; wherein a plurality of separated sub-bondings is formed in the associated bonding area between the second component and the interconnecting component.
A window for a vehicle with a main window pane having a vent window opening, and a vent window assembly mounted to the main window pane. The vent window assembly comprises: a movable vent window pane adapted for closing the vent window opening in closed state of the vent window assembly; a first vent window frame assembly comprising a first support frame arranged on a first surface of the main window pane; and a second vent window frame assembly comprising a second support frame arranged on a second surface of the main window pane, wherein the second vent window frame assembly is rigidly attached to the first vent window frame assembly at the vent window opening such that the first and second vent window frame assemblies fasten each other at the main window pane.
A door frame unit for integration into a fuselage of an air vehicle includes at least one door frame component, wherein the door frame unit includes an inner frame and an outer frame surrounding the inner frame, wherein the inner frame defines a door frame opening with horizontal edges and vertical edges, in which a door is mountable, wherein a plurality of cross struts extend between the inner frame and the outer frame and are rigidly connected to the inner frame and the outer frame, and wherein the outer frame runs at an angle to the cross struts at least at areas directly neighboring corners of the inner door frame.
The invention proposes a mould for producing a hot-formed fibre composite component, having a forming tub with a base, a peripheral edge and a tub opening which faces away from the base and is delimited by the edge, having a forming mould, which is arranged in the forming tub, for applying a preform, and having a clamping frame which supports an elastic membrane and has a lower boundary surface for application on an upper boundary surface of the edge, wherein the edge and the clamping frame are designed to establish a fluid-tight connection with each other, so that the forming tub with the applied clamping frame can be evacuated by removal of air by suction through a suction connection arranged in the forming tub, wherein the membrane is designed to cling to a preform located in the forming tub and adjacent, free base regions when the forming tub is evacuated in the direction of the base of the forming tub, so that the preform is pressed onto the forming mould, and wherein the mould is heat-resistant up to a curing temperature of at least 200°C.
A method and system for determining a position of a transmitter includes synchronizing receivers by forwarding a list of measurement parameters from a central control unit to the receivers, wherein the list of measurement parameters contains a multiplicity of measurement time intervals, measuring signals by the receivers using the list of measurement parameters, forwarding data relating to the measured signals from the receivers to the central control unit, wherein the data relating to the measured signals contain a measurement time and a measurement position of the measured signal, and evaluating the forwarded data to determine the position of the transmitter by the central control unit.
A rotorcraft comprising a fuselage forming at least one lower lateral fuselage compartment with at least a first fitting, a second fitting, and a third fitting; and at least one non-retractable wheel-type landing gear that comprises: at least one wheel; a shock absorber with a shock absorber tube having an open end and an axially opposed closed end, and a shock absorber rod telescopically mounted to the shock absorber tube via the open end; a first fixation provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation provided close to the closed end on the shock absorber tube and connected to the third fitting.
A cargo hook device with a housing that accommodates at least partly a cargo hook and a cargo hook blocking and releasing mechanism that is adapted for blocking, in a locked state, the cargo hook in a closed position and for releasing, in a released state, the cargo hook to enable rotation of the cargo hook between the closed position and an open position; wherein the cargo hook blocking and releasing mechanism comprises a blocking arm that blocks, in the locked state, movement of the cargo hook, an activatable locking lever that blocks, in the locked state, movement of the blocking arm, and an activatable safety locking device that blocks, in the locked state, movement of one of the cargo hook, the blocking arm, or the activatable locking lever.
A hollow conductor has a first flange, a second flange, a flexible hollow conductor section, and a first fastening unit. The flexible hollow conductor section is electrically connected both to the first flange and to the second flange in such a way that a radio-frequency signal (RF signal) can be transmitted from the first flange to the second flange or vice versa via the flexible hollow conductor section. The flexible hollow conductor section has a surface, and a first depression is arranged in the surface. The first fastening unit is connected to the first flange. The first fastening unit rests against the surface of the flexible hollow conductor section in a first overlap region in a longitudinal direction of the flexible hollow conductor section and engages in the first depression of the flexible hollow conductor section and thereby fixes the flexible hollow conductor section with respect to the first flange.
FRAUNHOFER-GESELLSCHAFT ZUR FÖRDERUNG DER ANGEWANDTEN FORSCHUNG E. V. (Germany)
AIRBUS DEFENCE AND SPACE GMBH (Germany)
Inventor
Esser, Dominik
Wührer, Christian
Abstract
The invention relates to a method for stabilising the frequency of a narrow-band Q-switched laser, in which method laser radiation from a seed laser (5) with a wavelength at which the laser pulses are to be generated is coupled into the laser resonator. A temporal intensity profile of laser radiation from the seed laser (5) coupled out of the laser resonator is detected, and, on the basis of the simultaneously detected temporal intensity profile, the optical resonator length of the laser resonator is controlled, by periodically varying same, to an approximately constant temporal average value in a control period between two laser pulses. During the time range in which the laser pulse is being generated, the optical resonator length of the laser resonator is changed from an initial value, that is known due to the previous control process, to a resonance value at which the laser resonator is in resonance with the wavelength of the seed laser (5) when the Q-switch (4) is switched, and, when said resonance value is reached, the Q-switch (4) is switched in order to generate a laser pulse. The method protects the element used to change the resonator length and yet makes it possible to stabilise frequency in a highly accurate manner with good a priori knowledge of the trigger time.
H01S 3/139 - Stabilisation of laser output parameters, e.g. frequency or amplitude by controlling the mutual position or the reflecting properties of the reflectors of the cavity
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific, research, navigation, surveying, photographic, cinematographic, audiovisual, optical, weighing, measuring, signalling, detecting, testing, inspecting, life-saving and teaching apparatus and instruments; Apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data; Computer software; Communication and networking software, Software; Data and file management and database software; Software for monitoring, analysing, controlling and running physical world operations; System and system support software, and firmware; Interfaces for computers; Interfaces for computers; Signal cables for IT, AV and telecommunication; Software algorithms for running and connecting video paths; Computers; Navigation, guidance, tracking, targeting and map making devices; Sensors, detectors and monitoring instruments; object detectors, Movement detectors. Scientific and technological services and research and design relating thereto; Industrial analysis; Industrial research; Design of computer hardware and software; Software development, programming and implementation; Science and technology services As well as Scientific and technical consultancy, in relation to the following goods: Scientific, research, navigation, surveying, photographic, cinematographic, audiovisual, optical, weighing, measuring, signalling, detecting, testing, inspecting, life-saving and teaching apparatus and instruments, Apparatus and instruments for recording, transmitting, reproducing or processing sound, images or data; Science and technology services As well as Scientific and technical consultancy, in relation to the following goods: Computer software, communication and networking software As well as Software, Software for data and file management and for databases, software for monitoring, analyzing, controlling and running physical world operations; Science and technology services As well as Scientific and technical consultancy, in relation to the following goods: System and system support software As well as firmware, Interface software, Interfaces (computing), Signal cables for IT, audiovision and telecommunications, software algorithms for running and connecting video paths; Science and technology services As well as Scientific and technical consultancy, in relation to the following goods: Computer, Navigation, guidance, tracking, targeting and map making devices, Sensors, Detectors As well as Surveillance apparatus and instruments, Object and movement detectors.
90.
Manufacturing method of a spacecraft including a marking of a surface
A method of manufacturing a spacecraft is disclosed including electing an outer cover material for the spacecraft, the outer cover material having an inner surface and an outer surface, the outer surface being electrically conductive, and the method further includes partially exposing the outer surface of the outer cover material to laser source to achieve a marking on the outer surface.
The present disclosure relates to a calibrated constellation simulator, a system and a method for calibrating and/or testing a star sensor assembled on a spacecraft. The calibrated constellation simulator comprises an optical device configured to project a defined star formation (IRF) of a star catalog onto a star sensor assembled on a spacecraft. Further, the calibrated constellation simulator comprises an alignment unit with a position and/or location reference (ARF) of the calibrated constellation simulator configured to detect a position and/or location of the calibrated constellation simulator in space, wherein the defined star formation (IRF) and the position and/or location reference (ARF) are in a first fixed calibrated rotation (QOSPS) with respect to one another. The calibrated constellation simulator improves the calibration of the star sensor as an independent calibration standard. The constellation simulator becomes a calibration standard.
A driverless ground vehicle for coupling to an aircraft has a vehicle base, a chassis with wheels that is arranged on the vehicle base, a control unit, a drive, an electrical energy store, and a coupling unit. The drive is coupled to the chassis for moving the wheels. The coupling unit is arranged on the vehicle base and carries an electrical line to be connected to the electrical energy store and has a first electrical connector at a distal end. The coupling unit is designed to move the first electrical connector for coupling to a second electrical connector. The control unit is connected to the drive and the coupling unit to control the drive to move the ground vehicle to the aircraft and to control the coupling unit to move the first connector into a predefinable position on the aircraft to establish an electrical connection to the second electrical connector.
A rotorcraft with a fuselage and a tail boom, comprising: a horizontal stabilizer mounted to the tail boom; rotor blades with rotor blade tips which form a virtual blade tip circle upon rotation around a rotor head; luminescent components provided on the rotor blade tips; and a blade tip illumination device comprising at least one light source integrated into the horizontal stabilizer and configured to emit a light beam toward the virtual blade tip circle for excitation of the luminescent components; wherein the luminescent components emit light in response to excitation via the emitted light beam, and wherein the emitted light forms during rotation of the rotor blade tips around the rotor head on the virtual blade tip circle a luminous ring.
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
F21K 2/00 - Non-electric light sources using luminescenceLight sources using electrochemiluminescence
94.
Method of Manufacturing a Component from a Composite Material with Locally Different Thicknesses
A method for producing a component having locally different thicknesses includes the steps of providing a first laminate, arranging a release layer on the first laminate, providing a second laminate with a second surface correlating with the first surface of the first laminate, placing the second laminate with the second surface on the first surface so that the release section is enclosed, joining the first with the second laminate by heating and/or pressing, guiding a cutting tool along one release section correlating with the release section, and so that the separating section is included, joining the first to the second laminate by heating and/or pressing, guiding a cutting tool along one contour in the second laminate that correlates with the separating section, so that one segment of the second laminate is completely detached, and removing the detached segment so that a recess is formed in each case.
B29C 51/14 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor using multilayered preforms or sheets
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
95.
Retaining and releasing device and assembly for spacecraft
A retaining and releasing device for spaceships retains and releases a body to/from a support structure. A releasing bolt keeps the releasable body and the support structure connected in a position for locking the retaining and releasing device. A locking device for locking the releasing bolt in the support structure has a case and a segmented ring. The case is movable axially relative to the releasing bolt and includes an end with a through-slot. A releasing system includes an actuator, a rod having the same orientation as the releasing bolt, with a locking pin, cooperating with the slot, and a compression spring. The actuator locks the rod in a position for locking the retaining and releasing device. The compression spring is in contact with the case of the locking device and disposed around the rod to rotate the rod. The device includes a system for removing the releasing bolt.
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Navigation, guidance, tracking, targeting and map making devices; measuring, detection and monitoring instruments, devices and controllers; audio/visual and photographic devices; enhancers; correctors; sensor systems consisting of a daylight camera and thermal imaging apparatus; optical and/or electronic vision systems for vehicles; optical instruments and enhancers and parts therefor; optical viewing devices; spotting scopes; thermal imaging apparatus; apparatus providing night vision; daylight cameras; night vision goggles; sensors; attachment lenses; objective and ocular lenses; observation eyepieces; distance measuring apparatus; laser range finders; laser targeting device; residual light image intensifier; day and night sights and attachments; target devices; target recognition devices and software; optical apparatus; sighting or simulation apparatus and instruments for shooting purposes; spare parts and accessories and software and firmware for all of the aforesaid goods; batteries; the aforesaid goods for use only in connection with or as part of optical and/or electronic sighting systems and/or equipment incorporated in military vehicles; none of the aforementioned goods for use in connection with the testing, monitoring or detection of fuels, chemicals and other substances. Installation and maintenance of data processing devices and computer hardware; consultancy in relation to all of the aforesaid services; adjustment, commissioning and service for the repair of electro-optical equipment; maintenance and repair of electro-optical devices and installations for third parties; installation and maintenance of electronic warfare vehicles and equipment and systems; installation, cleaning, repair and maintenance services for electronic warfare equipment; consultancy in relation to repair, maintenance and installation and repair, maintenance and installation in relation to all of the following goods: navigation, guidance, tracking, targeting and map making devices, measuring, detection and monitoring instruments, devices and controllers, audio/visual and photographic devices, enhancers, correctors, sensor systems consisting of a daylight camera and thermal imaging apparatus, optical and/or electronic vision systems for vehicles, optical instruments and enhancers and parts therefor, optical viewing devices, spotting scopes, thermal imaging apparatus, apparatus providing night vision, daylight cameras, night vision goggles, sensors, attachment lenses, objective and ocular lenses, observation eyepieces, distance measuring apparatus, laser range finders, laser targeting device, residual light image intensifier, day and night sights and attachments, target devices, target recognition devices and software, optical apparatus, sighting or simulation apparatus and instruments for shooting purposes, spare parts and accessories and software and firmware for all of the aforesaid goods, batteries; the aforementioned services only for use in connection with or as part of optical and/or electronic sighting systems and/or equipment integrated into military vehicles; none of the aforementioned services for use in connection with the testing, monitoring or detection of fuels, chemicals and other substances. Scientific and technological services and scientific and technical consultancy relating to all of the following goods: navigation, guidance, tracking, targeting and map making devices, measuring, detection and monitoring instruments, devices and controllers, audio/visual and photographic devices, enhancers, correctors, sensor systems consisting of a daylight camera and thermal imaging apparatus, optical and/or electronic vision systems for vehicles, optical instruments and enhancers and parts therefor, optical viewing devices, spotting scopes, thermal imaging apparatus, apparatus providing night vision, daylight cameras, night vision goggles, sensors, attachment lenses, objective and ocular lenses, observation eyepieces, distance measuring apparatus, laser range finders, laser targeting device, residual light image intensifier, day and night sights and attachments, target devices, target recognition devices and software, optical apparatus, sighting or simulation apparatus and instruments for shooting purposes, spare parts and accessories and software and firmware for all of the aforesaid goods, batteries; design and development of computer hardware and software for navigation, guidance, tracking, targeting and map making devices, measuring, detection and monitoring instruments, devices and controllers, audio/visual and photographic devices, enhancers, correctors, sensor systems consisting of a daylight camera and thermal imaging apparatus, optical and/or electronic vision systems for vehicles, optical instruments and enhancers and parts therefor, optical viewing devices, spotting scopes, thermal imaging apparatus, apparatus providing night vision, daylight cameras, night vision goggles, sensors, attachment lenses, objective and ocular lenses, observation eyepieces, distance measuring apparatus, laser range finders, laser targeting device, residual light image intensifier, day and night sights and attachments, target devices, target recognition devices and software, optical apparatus, sighting or simulation apparatus and instruments for shooting purposes, batteries; the aforementioned services only for use in connection with or as part of optical and/or electronic sighting systems and/or equipment integrated into military vehicles; none of the aforementioned services for use in connection with the testing, monitoring or detection of fuels, chemicals and other substances.
97.
Active trim system of a flight control system of an aircraft
An active trim system of a flight control system of an aircraft that transmits a tactile feel to a pilot of the aircraft in response to a manoeuvre. The active trim system includes: a manual control member (6) an elastic deformation means (1) and a reversible actuator (2), intermediate linkage member (4) and a controller. The actuator (2) includes a rod (5) and a motor (3) parallel to the elastic deformation means (1) and is movable by the motor (3) and by the motion of the manual control member (6). The intermediate linkage member (4) is linked to the manual control member (6) between the manual control member (6) and the elastic deformation means (1) and the reversible actuator (2), a controller configured to: move the reversible actuator (2) to a predetermined zero position, and to provide stiffness against a displacement of the intermediate linkage member (4).
A collapsible self-supporting human and/or non-human cargo transport device for use with a rotorcraft, comprising: an inner cargo storage area for accommodating human and/or non-human cargo for transportation; a self-supporting skeletal frame, and collapsible cargo securing means mounted to the self-supporting skeletal frame for delimiting the inner cargo storage area. The self-supporting skeletal frame comprises a collapsible platform support structure, a collapsible spreading structure, a telescopic rod connecting the collapsible platform support structure to the collapsible spreading structure, an attachment connected to the telescopic rod to enable attachment of the self-supporting skeletal frame to a rotorcraft, and a plurality of tensioning cables connecting the attachment to the collapsible spreading structure and the collapsible platform support structure.
The present invention relates to devices for discharging fluid off an aircraft. More particularly, the present invention relates to discharging devices for firefighting aircraft. In addition, the present invention also relates to a firefighting system comprising said device, an aircraft comprising said firefighting system and a method for discharging fluid off an aircraft by means of said firefighting system.
A62C 3/02 - Fire prevention, containment or extinguishing specially adapted for particular objects or places for area conflagrations, e.g. forest fires, subterranean fires
A62C 31/28 - Accessories for delivery devices, e.g. supports
B64D 1/16 - Dropping or releasing powdered, liquid or gaseous matter, e.g. for fire-fighting
100.
RESOURCE MANAGEMENT FOR SATELLITE-BASED OBSERVATION
An observation system for observing a region of interest. The observation system has multiple mobile sensor carrier platforms and a resource allocation unit. The mobile sensor carrier platforms may be configured as satellites having a sensor signal emitter and/or a sensor signal receiver, for example. The resource allocation unit is configured to assign tasks to the sensor carrier platforms on the basis of various criteria in order to improve the efficiency for carrying out the tasks and the completion rate.
