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MISCELLANEOUS

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244 - Aeronautics and astronautics

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Class / Patent application numberDescriptionNumber of patent applications / Date published
244001000 Noise abatement 84
244001000 Lightning arresters and static eliminators 33
244001000 Trailing devices 15
Entries
DocumentTitleDate
20090194634UNMANNED VEHICLE HAVING A CAMOUFLAGE APPARATUS - An unmanned vehicle has a camouflage apparatus which simulates a characteristic of an animal. This allows effective camouflage to be achieved despite the unmanned vehicle being clearly visible.08-06-2009
20080258006High altitude structures control system and related methods - A system and method is described generally for providing a high altitude structure including an elongated structure extending substantially skyward from the ground. The elongated structure at least partially supported by buoyancy effects. The system and method also include a gas having a density that is less dense than that of the atmosphere outside of the elongated structure; the gas is disposed in one or more voids of the elongated structure. The system and method further include at least one control device coupled to the elongated structure and used to control the motion of the elongated structure, the control device not being directly coupled to the surface of the Earth.10-23-2008
20100270427BIRD COLLISION PREVENTION DEVICE FOR AN AIRCRAFT - A bird collision prevention device with a plurality of circular interior support members with decreasing diameters concentrically disposed along an axis, a plurality of outer ribs welded tangentially to the circular interior support members forming a like conical shape mesh body, a plurality of bolts or latches securable to the circular interior support member with the largest diameter and the cowling, and wherein the mesh body is secured to the cowling of the turbine engine enabling a tapered end of the mesh body to extend away from the turbine engine.10-28-2010
20090242695SECURING EMERGENCY AND SAFETY EQUIPMENT ON AIRCRAFT - An emergency equipment system comprising an elongate member, an emergency equipment package, and a cutter. The elongate member may have a first end and an angled end. The emergency equipment package may have a sleeve on one side capable of receiving the elongate member from the angled end. The cutter may be attached to a side of the elongate member and may be capable of cutting the sleeve.10-01-2009
20100224725System and method for powering an aircraft using radio frequency signals and feedback - A system and method are described for powering an aircraft using radio frequency (“RF”) signals. For example, a method according to one embodiment of the invention comprises: positioning an antenna array beneath or on the road surface of a roadway, the antenna array configured to transmit RF signals responsive to RF processing logic and/or circuitry; coupling a rectenna array to an aircraft, the rectenna array configured to receive the RF signals transmitted from the antenna array and to generate power from the RF signals; providing feedback signals from the aircraft to the RF processing logic and/or circuitry, the feedback signals including channel state information (CSI) defining a current state of the channels between the antenna array and the rectenna array, the RF processing logic and/or circuitry using the channel state information to adjust the RF signal transmissions from the antenna array to improve the efficiency of the power generated by the rectenna array; and using the power generated by the rectenna array to power the aircraft.09-09-2010
20100001127METHOD FOR CONTROLLING THE INTERNAL PRESSURE IN AN AIRCRAFT - The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve. During a too steep descent or in case of failure of the air conditioner of the craft, the flap directs air into the craft and thus adapts the internal pressure to the external pressure as soon as it exceeds the internal pressure. Thus, a negative pressure relief valve is advantageously not required and a size thereof can be considerably reduced respectively.01-07-2010
20090065638Apparatus for voice communication between persons inside and persons outside an aircraft - An apparatus for facilitating voice communication between persons outside an aircraft and persons inside an aircraft, is disclosed, comprising: an external control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons in said aircraft; receiving means for receiving voice information from persons in said aircraft; and amplifying means for enabling said voice information to be heard; and an in-aircraft control unit comprising: voice sensing means; transmitting means for transmitting voice information to persons external to said aircraft; receiving means for receiving voice information from persons external to said aircraft; and amplifying means for enabling said voice information to be heard.03-12-2009
20090127386METHODS AND SYSTEMS FOR IMPROVING AIRCRAFT VISIBILITY - A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft.05-21-2009
20080272233Method and system for generating renewable energy - A method, system and apparatus for the generation of energy. The method system and apparatus can include one or more airships that collect solar energy and convert it into electricity. An array of airships may be used so as to increase the collection rates of solar energy. The array of airships may include an airship that receives and stores electricity from the other airships in the array. Additionally, the solar energy may be transmitted to a terrestrial collection and distribution station.11-06-2008
20080217472ROCKET-POWERED VEHICLE RACING REALITY SYSTEM - An aerial vehicle race and reality system for entertaining spectators wherein computer-generated images are optionally provided to at-least partially define a race-course.09-11-2008
20100019084Aerospace manufacturing system - An Aerospace Manufacturing System is disclosed, which comprises methods and apparatus for reducing the manufacturing costs in an aerospace product. In one embodiment, this method is accomplished by designing the aerospace product to use non-aerospace industry components and by maximizing the use of said plurality of readily commercially available, non-aerospace industry components. These commercially available, non-aerospace components are sometimes referred to by the term “commercial off the shelf” or “COTS” products.01-28-2010
20090173822Distributed infrared countermeasure installation for fixed wing aircraft - A distributed aircraft defense system involving infrared countermeasures is installed in a distributive fashion for commercial aircraft, typically fixed wing aircraft, in which maintenance downtime is minimized due to the ability to access, remove, test, fix and/or replace individual modules within the distributed system.07-09-2009
20110180661Optically Reconfigurable Radio Frequency Antennas - Optically reconfigurable radio frequency antennas for use in aircraft systems and methods of its use are disclosed. In one embodiment, the antenna includes a surface-conformal reflector that includes optically addressable carbon nanotubes. The nanotubes can be combined with light-sensitive materials so that exposure to light of the correct wavelength will switch the nanotubes back and forth between a metallic and non-metallic state. The antenna has a transmitter that radiates a radio frequency signal in the direction of the surface illuminator and an addressable optical conductor to illuminate the nanotubes with one or more optical signals. When the domains are illuminated they switch portions of the carbon nanotubes between its non-metallic states and metallic states to reflect the radiated radio frequency signal.07-28-2011
20100025527SURGICALLY IMPLANTED MICRO-PLATFORMS AND MICROSYSTEMS IN ARTHROPODS AND METHODS BASED THEREON - A method is provided for producing an arthropod comprising introducing a microsystem such as a MEMS device into an immature arthropod under conditions that result in producing an adult arthropod with a functional microsystem permanently attached to its body. A method is also provided for producing a robotic apparatus. The method can comprise introducing a microsystem such as a MEMS device into an immature arthropod under conditions that result in producing a robotic apparatus with the microsystem permanently attached to the body of the adult arthropod.02-04-2010
20120138741Method And Device For Aiding The Localization Of An Aircraft Wreck Submerged In A Sea - Method and device for aiding the localization of an aircraft wreck submerged in a sea.06-07-2012
20130020435DATA ACQUISITION SYSTEM AND APPARATUS - A data acquisition system comprising: an aircraft ejectable seat; a flight data recorder removeably attached to the ejectable seat; a data connector in signal communication with the flight data recorder, and configured to removeably connect to an aircraft's data bus. A data acquisition apparatus comprising: a flight data recorder; a data connector in signal communication with the flight data recorder, and configured to removeably connect to an aircraft's data bus; and where the flight data recorder is configured to removeably attach to an ejectable aircraft seat.01-24-2013
20080217473ROCKET-POWERED VEHICLE RACING COMPETITION - A method for racing rocket-powered vehicles directly against one another is provided in which a first rocket-powered vehicle simultaneously races against a second rocket-powered vehicle to be the first to complete a race course. The method may include the first and second rocket-powered vehicles performing a pre-determined maneuver while proximate a group of spectators, and/or the rocket-powered vehicles strategically performing the steps of gliding and boosting the flight of their rocket-powered vehicle in accordance with a pre-determined maximum fuel criteria. The method further may include permitting spectator interaction with participants of the racing competition and enabling spectators to compete with actual participants via virtual vehicles. The method may also include the rocket-powered vehicles performing a refueling operation. The method may further include providing audible or visual identifiers of the vehicles. In addition, the method may include providing safety data to ensure safe separation between competing vehicles.09-11-2008
20080217471INTELLIGENT AIRCRAFT SECONDARY POWER DISTRIBUTION SYSTEM THAT FACILITATES CONDITION BASED MAINTENANCE - An electrical power distribution system comprises a solid state power controller in communication with an aircraft system main data bus via a gateway module and a condition based maintenance module in communication with the solid state power controller via a communication network distinct from the main data bus. A method of load/feeder health assessment for an electrical power distribution system includes applying a controlled excitation to a load; sampling information from the load/feeder system for the load; characterizing a normal behavior of the load/feeder system for the load; determining if the load characteristics are within the normal behavior profile for the load; and shutting down power to the load if load characteristics are not within the profile when immediate action is indicated or generating a health message for the load when immediate action is not required.09-11-2008
20130206901SMALL ARMS CLASSIFICATION/IDENTIFICATION USING BURST ANALYSIS - Systems and methods are provided for differentiating weapon fire from targets on the ground to an aircraft such that appropriate countermeasures can be taken. A plurality of shots from a target on the ground is detected from a sensor in the aircraft. Shots belonging to a single burst are correlated. A firing characteristic of the plurality of shots in the burst is computed. A weapon type is determined for the plurality of shots based on the firing characteristic.08-15-2013
20130043342MULTIFUNCTIONAL DE-ICING/ANTI-ICING SYSTEM - A de-icing/anti-icing system including at least two conductive structures embedded in an article that includes an outer surface designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. A first of the conductive structures includes a first conductive nano structure and a second of the conductive structures includes a second conductive nano structure. A conductive property of the first of the conductive structures differs from a conductive property of the second of the conductive structures. The first conductive nano structure serves as a heating conductor and the second conductive nano structure serves as a heating element. The first and second conductive nano structures are embedded in a common plane of a resin layer forming the outer surface.02-21-2013
20100108804AIRCRAFT ASSEMBLY AND METHOD FOR MANUFACTURING THE SAME - An aircraft assembly having improved durability and capable of providing good lightning protection is provided. Provided is an aircraft assembly (05-06-2010
20130087655Precipitation Static Charge Drain System For An Aircraft Window - A static charge drain system for an aircraft window includes a resistive probe penetrating an outer ply of the aircraft window, a first end of the probe being exposed at an outer surface of the outer ply of the aircraft window. A second end of the probe penetrates an inner surface of the outer ply of the aircraft window. A conductive drain element is disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and is electrically connected between the second end of the probe and a ground point of the aircraft window.04-11-2013
20120181384DEVICE FOR PROTECTING PIPING FROM LIGHTNING - A device for protecting piping from lightning. The piping includes tubular metal sections connected to each other by connection parts, a first portion of the connection parts being plastic material parts and a second portion of the connection parts being metal parts.07-19-2012
20090266935SHELL ARRANGEMENT AS WELL AS AIRCRAFT OR SPACECRAFT - The present invention provides a shell arrangement as well as an aircraft or spacecraft comprising such a shell arrangement. The shell arrangement comprises a first lightning conductor layer for conducting lightning energy and a fibre composite layer supporting the first lightning conductor layer. Furthermore, the shell arrangement comprises a first electrical connection for connecting a first electrical component with the first lightning conductor layer. The advantage resulting according to the invention is that the lightning conductor layer fulfils a double function: on the one hand it serves to conduct lightning energy and on the other hand it forms a portion of a circuit for operating the first electrical component. For this reason, the need for electrical wiring in the airplane is reduced, in turn resulting in a weight reduction for the aircraft or spacecraft.10-29-2009
20110017867COMPOSITE MATERIALS - A composite material, the composite material comprising a prepreg, said prepreg comprising at least one polymeric resin and at least one conductive fibrous reinforcement, electrically conducting particles dispersed in the polymeric resin and a top layer of a metal-coated carbon fibre comprising a further resin component, wherein the metal comprises one or more metals selected from nickel, copper, gold, platinum, palladium, indium and silver.01-27-2011
20110284688ROTOR PROVIDED WITH A DEVICE FOR PROTECTING IT AGAINST LIGHTNING, AND AN AIRCRAFT PROVIDED WITH SUCH A ROTOR11-24-2011
20100001126COATING OF AN AIRCRAFT SEAT MOUNTING RAIL OR A AIRCRAFT SEAT STUD - A mounting rail that is designed for mounting installations in an aircraft, with the mounting rail being coated with a coating made of a coating material, wherein the coefficient of friction between the coating material and a material of an element to be mounted is lower than the coefficient of friction between a material from which the non-coated mounting rail is made and a material of an element to be mounted. The coating material may be provided with a conductive additive.01-07-2010
20100320315LIGHTNING-PROTECTION FASTENER - Provided is a lightning-protection fastener that is capable of reliably preventing peeling off of an insulation layer during the operation of an aircraft and of improving the anti-lightning-strike capability and reliability. There is a lightning-protection fastener that fastens a skin of an aircraft and a structural member positioned inside the skin, in which an insulation layer is melt adhered so as to cover one end surface of a head portion and also to mechanically engage with a fastener-side engagement portion (engagement portion) formed on the end surface.12-23-2010
20120292439ARTICLE WITH DE-ICING/ANTI-ICING FUNCTION - A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.11-22-2012
20090184199Shielding arrangement for lines, in particular electrical lines, in aircraft - A shielding arrangement for the lightning protection of electrical lines and components in an aircraft includes a protected installation space for receiving the lines that is arranged in the region of a floor framework, at least one delimiting surface of the installation space being provided at least in certain regions with an electrically conductive shielding, the at least one delimiting surface of the installation space being formed with at least one floor panel and a further delimiting surface of the installation space being formed with at least one ceiling panel.07-23-2009
20090050735SYSTEMS AND METHODS RELATED TO ELECTROMAGNETIC ENERGY DISSIPATION - Embodiments of the present invention relate generally to systems and methods related to electromagnetic energy dissipation, including the dissipation of static electricity. One aspect of the invention is directed toward an electromagnetic dissipation system that includes a conductive material, a protective element, and a base element. The conductive material is coupled between a portion of the outer surface of the protective element and a portion of the outer surface of the base element to form a modular dissipation system. Other aspects of the invention are directed toward a vehicle system that includes a receiving surface, a conductive element, and a protective element. The conductive element is (a) coupled between a portion of the receiving surface of the vehicle and a portion of the outer surface of the protective element, and/or (b) embedded in the portion of the receiving surface.02-26-2009
20100224724AIRCRAFT ASSEMBLY - Provided is an aircraft assembly equipped with a lightning protection structure that is not easily destroyed by lightning current and that is highly reliable. In an aircraft assembly including a skin (09-09-2010
20100276536LIGHTNING PROTECTION SYSTEM AND AIRCRAFT COMPRISING SUCH A SYSTEM - An anti-lightning system for a composite structure having an external surface configured to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners attaching this strip to the aforementioned structure. According to the disclosed embodiments, with this structure including holes configured to accept the fastenings for the strip, at least some these fastenings comprise an attachment element that attaches the lightning to this structure. This attachment element is configured to be inserted in the hole with its upper part substantially flush with the external surface of the structure, this attachment element being in electrical contact with the electrically conducting strip. The electrically conducting strip is configured to be positioned on the opposite side of the structure to the external surface and electrically earthed.11-04-2010
20100219287PROTECTION AGAINST DIRECT LIGHTNING STRIKES IN RIVETED AREAS OF CFRP PANELS - The invention relates to a metalization structure of aircraft panels and process for obtaining such structure, such that it comprise a structure of a panel (09-02-2010
20100213312Distributing Power in Systems Having a Composite Structure - Systems and methods to distribute power in a system having a composite structure are provided. A particular aircraft includes a fuselage having a composite skin. The composite skin includes a first resin and a plurality of fibers. The fuselage also includes an expanded conductive patch bonded to an interior surface of the composite skin by a second resin. The expanded conductive patch is in electrical contact with the plurality of fibers. The fuselage also includes a connector in electrical contact with the expanded conductive patch.08-26-2010
20120145825LIGHTNING AND CORROSION PROTECTION ARRANGEMENT IN AN AIRCRAFT STRUCTURAL COMPONENT - A lightning and corrosion protection arrangement for a joint between an outer metallic part (06-14-2012
20110259999LIGHTNING PROTECTION ARRANGEMENT FOR AN ELECTRONIC UNIT - Lightning protection arrangement for diverting a current, caused by a lightning strike, from an electronic unit which is fitted to an aerodynamic fairing of an aircraft. The device comprises an electrically conductive mounting plate which is arranged on an outer side of a CFRP sandwich panel of the aerodynamic fairing. Furthermore, the device has an electrically conductive rear plate which is arranged on an inner side of the CFRP sandwich panel of the aerodynamic fairing and is connected electrically to the mounting plate. In this respect, a first group of attachment means provided for the electronic unit connects the electrical unit electrically to the rear plate. An electric current generated during a lightning strike is diverted with low resistance from the electrical unit via the rear plate and the mounting plate onto the fuselage of the aircraft.10-27-2011
20110073708Composite Barrel Sections for Aircraft Fuselages and Other Structures, and Methods and Systems for Manufacturing Such Barrel Sections - Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are disclosed herein. A composite section configured in accordance with one embodiment of the invention includes a skin and at least first and second stiffeners. The skin can include a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis. The first stiffener can include a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin. The second stiffener can include a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin. A method for manufacturing a section of a fuselage in accordance with one embodiment of the invention includes positioning a plurality of uncured stiffeners on a mandrel assembly. The method can further include applying a plurality of fiber tows around the plurality of uncured stiffeners on the mandrel assembly.03-31-2011
20120043415BOND LEAD - A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibres coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibres and others forming bridges between adjacent fibres. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank.02-23-2012
20090166468METHOD AND APPARATUS FOR SKIN MAPPING OF LIGHTNING DETECTION SYSTEM - A lightning strike to an aircraft causes problems in existing aircraft equipment. To offset the problem, weather equipment can be used, but the weather equipment is prone to noise interference with existing aircraft equipment. By effectively positioning the weather equipment, the present invention solves the noise interference problem. In particular, the process detects an environment event, using weather equipment, on the subject aircraft. Next, the system identifies an origination point of noise, resulting from the detected environment event, in internal aircraft equipment. After identifying the origination point of the noise, the system makes a measurement to determine if the noise is interfering with a signal of the internal aircraft equipment. If interference exists, an operator cancels the noise and adjusts the location of the weather equipment in an external surface of the subject aircraft in such a manner as to provide an interference free environment for the internal aircraft equipment.07-02-2009
20110049292LIGHTNING STRIKE PROTECTION - An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm/square.03-03-2011
20120119022APPLICATION OF INSULATING COATING - Systems and methods for discontinuously applying an insulating primer to a carbon fiber reinforced plastic (CFRP) component are disclosed. In one embodiment, a method for mitigating electrical surface discharges from a CFRP component includes first applying an insulating primer to a metallic component. Next, an insulating primer is applied discontinuously to the CFRP component adjacent the metallic component. The discontinuous application of the insulating primer forms a primed portions and unprimed portions. The unprimed portions are configured to enable electrostatic dissipation.05-17-2012
20120126054LIGHTNING PROTECTION FOR COMPOSITE AIRCRAFT STRUCTURES - Lightning protection system (05-24-2012
20120160960LIGHTNING-RESISTANT FASTENER - There is provided a lightning-resistant fastener that can secure sufficient lightning-resistance performance at low cost and realize efficiency of field work and improvement of reliability. An insulating coat film 06-28-2012
20120074257LIGHTNING-RESISTANT FASTENER, CAP, AND METHOD OF MOUNTING LIGHTNING-RESISTANT FASTENER - There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A hole 03-29-2012
20110226896LIGHTNING-RESISTANT FASTENER, CAP, FASTENER MEMBER, AND METHOD FOR ATTACHING LIGHTNING-RESISTANT FASTENER - A lightning-resistant fastener, a cap, a fastener member, and a method for attaching the lightning-resistant fastener are provided, which enhance workability and quality stability besides reliably securing an insulating property, and can lead to enhancement in safety of an airframe and reduction in manufacturing cost. A head portion 09-22-2011
20120091269LIGHTNING STRIKE PROTECTION IN AIRCRAFT - Lightning strike protection in aircraft: the invention refers to a lightning strike protection system for fuel tank access covers (04-19-2012
20130009001Electric Charge Dissipation System for Aircraft - A method and apparatus comprising a first composite layer and a second composite layer in which the second composite layer is associated with the first composite layer. The first composite layer and the second composite layer form a structure. The second composite layer has a conductivity configured to dissipate an electric charge on a surface of the structure and limit a flow of an electrical current in the second composite layer in which the electrical current is caused by an electromagnetic event.01-10-2013
20130015292Decorative Decal System for an AircraftAANM Zielinski; EdwardAACI KentAAST WAAACO USAAGP Zielinski; Edward Kent WA USAANM Iwamoto; James T.AACI RentonAAST WAAACO USAAGP Iwamoto; James T. Renton WA US - A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material.01-17-2013
20080251636AIRCRAFT THAT COMPRISES A STRUCTURE THAT ENSURES THE STRUCTURAL AND ELECTRICAL FUNCTIONS - An aircraft includes a structure with structural elements (10-16-2008
20130119195MANUFACTURING METHOD FOR COMPOSITE MATERIAL STRUCTURAL COMPONENT FOR AIRCRAFT AND ITS STRUCTURAL COMPONENT - A method for manufacturing a structural component includes a first step of attaching at least one conductive member to a surface of a base material made of a composite material and a second step of forming the base material by conducting electricity to part or the whole of the conductive member to generate heat and/or making an assembly of the structural component by conducting electricity to part or the whole of the conductive member to generate heat. Part or the whole of the conductive member contained in the structural component produced in the first and second steps serves as a member giving to the aircraft at least one of a lightning strike protection function, an anti-icing and deicing function and an electromagnetic interference shielding function.05-16-2013
20110315818Static Dissipative Fuel Tank Coatings and Methods - There is provided a method for mitigating static discharge in a fuel container. The method provides a static dissipative coating having a volume resistivity of 1.0×1012-29-2011
20130043343METHOD OF PROCESSING ACOUSTIC WAVES EMITTED AT THE OUTLET OF A TURBO ENGINE OF AN AIRCRAFT WITH A DIELECTRIC-BARRIER DISCHARGE DEVICE AND AIRCRAFT COMPRISING SUCH A DEVICE - A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discharge device so as to emit an electric wind in a direction of acoustic waves so as to attenuate the acoustic waves. An aircraft can include such a dielectric barrier discharge device.02-21-2013
20130032664COUNTER-TORQUE DEVICE FOR A HELICOPTER - A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.02-07-2013
20100044505HELICOPTER BLADE VORTEX INTERACTION NOISE REDUCING METHOD AND DEVICE - The present method is characterized by providing the rotor blade with a tab 02-25-2010
20100108807TETHERED HOVERING PLATFORM - The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution. The system components and manufacturing cost is presented in comparison to current systems using active stabilization05-06-2010
20100108805Aircraft Landing Gear Provided With At Least One Noise Reducing Means - The invention relates to a landing gear including a noise reducing means (05-06-2010
20130026288Aircraft Comprising At Least One Net For Reducing Aerodynamic Noise From A Structural Element Of Said Aircraft - The invention relates to an aircraft comprising at least one net for reducing aerodynamic noise from a structural element of said aircraft. According to the invention, the flexible net (01-31-2013
20100108806Hybrid propulsive engine including at least one independently rotatable propeller/fan - One aspect relates to a method of reducing noise for an aircraft. The method includes determining a mode of operation of the aircraft or the engine. The method also includes controlling a hybrid jet engine, based on the mode of operation, to at least partially use electrically generated torque to generate thrust.05-06-2010
20100065680DEVICE WITH PLANE JETS FOR REDUCING THE NOISE GENERATED BY A JET AIRCRAFT - The invention relates to an aircraft engine having a longitudinal axis (XX′), comprising a wall (03-18-2010
20100006697LOW NOISE AIRCRAFT - A low noise aircraft which can reduce engine noise on the ground sharply at the time of take-off and landing by utilizing a well-known mechanism. By utilizing a thrust deflection means constituted of a well-known mechanism for making the direction of thrust variable, exhaust direction of an engine is deflected to the upper side (upward) of the course direction (flight direction) of the aircraft so that the maximum propagation direction of the engine jet exhaust noise is kept away from the ground, thus reducing the engine noise level on the ground at the time of aircraft take-off and landing. In particular, when the thrust deflection type exhaust nozzle (01-14-2010
20100006696Landing gear noise reduction assembly - An aircraft noise reduction apparatus including an aircraft landing gear assembly (01-14-2010
20090302154Material for absorbing noise in aircraft - The invention relates to a material for absorbing noise in aircraft, comprising at least one barrier layer and at least one absorptive layer. The barrier layer is provided with an elastomeric material having a minimum specific density of 1 and a mass per unit area of 1.3 kg/m12-10-2009
20130056581Rijke Tube Cancellation Device for Helicopters - An acoustic signature reduction system for application typically on an aircraft. The acoustic signature reduction system uses a controller, power supply, and a thermo-acoustic tube such as a Rijke tube or Sondhauss tube to generate a cancellation noise of equal amplitude and inverted to that of noise generated by rotor blades when rotating. Acoustic signature reduction system can use a damping valve to make an intermittent cancellation sound to match the n/rev signature of the rotor blades with respect to a given reference location. The n/rev timing is different depending on the reference location therefore a cone of silence is created. A forced air unit may also be used to modify the phase of the cancellation noise in order to move the cone of silence around the aircraft.03-07-2013
20080296431NOISE CONTROLLED TURBINE ENGINE WITH AIRCRAFT ENGINE ADAPTIVE NOISE CONTROL TUBES - An aircraft turbine engine with a takeoff fan speed and a landing fan speed, the aircraft engine includes a fan duct with a HQ (Herschel-Quincke) acoustic control noise reduction tube. The acoustic control noise reduction tube contains a movable frequency tuner obstruction. The movable frequency tuner obstruction is movable within the acoustic control noise reduction tube, with the movable frequency tuner obstruction movable along a fixed tube path length between a first takeoff frequency obstruction tube path location, and a second landing frequency obstruction tube path location, with the frequency tuner obstruction positioned at the first takeoff frequency location with the takeoff speed, and the frequency tuner obstruction positioned at the second landing frequency location with the landing speed to reduce noise.12-04-2008
20090184200VIBRATION DAMPING FOR WING-TO-BODY AIRCRAFT FAIRING - A wing-to-body fairing for aircraft is formed from a sandwich structure having integrated vibration damping.07-23-2009
20090078820WING-TO-BODY FAIRING - In one embodiment, a wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in at least one of an aircraft and a spacecraft comprises a honeycomb center comprising a cavity which is substantially filled with foam material.03-26-2009
20090212158Aircraft Systems with Shape Memory Alloy (SMA) Actuators, and Associated Methods - Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. In another embodiment, an activatable link can be positioned between the actuator and the deployable device, and can have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.08-27-2009
20100170984ENGINE ASSEMBLY FOR AIRCRAFT WITH SLIDING NANCELLE - An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.07-08-2010
20120001022JET ENGINE INSTALLATION - Noise generated by a gas turbine engine 01-05-2012
20110284689AIRCRAFT CABIN PANEL FOR SOUND REDUCTION - The present invention relates to an aircraft cabin panel for sound reduction in an interior space. The invention in particular also relates to an aircraft comprising an interior lining with sound-absorbing and sound-reducing panels. In order to provide a panel that is optimized in terms of the design space required by it and in terms of its weight, for use in aircraft, which panel provides improved sound reduction and sound absorption characteristics, an aircraft cabin panel for sound reduction in an interior space is provided, which aircraft cabin panel in at least one region comprises a sandwich construction with a core layer, a first covering layer and a second covering layer. The core layer comprises sound absorbing open-pore core material. The first and the second covering layer are connected to the core layer in a planar fashion. The first covering layer is arranged towards the sound waves to be absorbed and the second covering layer is arranged opposite the first covering layer. The first covering layer is designed so as to be acoustically transparent.11-24-2011
20110133025ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE - This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin (06-09-2011
20120097791Autonomous Slat-Cove-Filler Device for Reduction of Aeroacoustic Noise Associated with Aircraft Systems - A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.04-26-2012
20120025016AIRCRAFT PROPELLER - A propeller for an aircraft is disclosed. The propeller has an odd number of unequally circumferentially spaced blades. The propeller may be provided as part of a contra-rotating propeller arrangement and/or aft of a pylon on an aircraft. The propeller has been found to reduce noise levels and to be efficient.02-02-2012
20090152395ABSORBENT STRUCTURE FOR ATTENUATING NOISE PARTICULAR BY A ROTOR-GENERATOR NOISE, AND A ROTOR DUCT INCLUDING SUCH A STRUCTURE - An absorbent structure for reducing the propagation of soundwaves emitted by noisy devices such as rotors or motors, the structure includes a rigid partition (06-18-2009
20100084508HIGH-LIFT DEVICE, WING, AND NOISE REDUCTION STRUCTURE FOR HIGH-LIFT DEVICE - The present invention provides high-lift devices, wings, and noise reduction structures for the high-lift devices capable of suppressing the occurrence of aerodynamic noise while restricting an increase in airframe weight. A high-lift device includes: a slat main body (04-08-2010
20100084507REMOVABLE AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The present invention relates to a nacelle (04-08-2010
20110139926Landing gear with noise reduction apparatus - An aircraft landing gear assembly comprises a landing gear (06-16-2011
20110139927PANEL FOR AN AIR INTAKE OF AN AIRCRAFT NACELLE THAT ENSURES OPTIMIZED ACOUSTIC TREATMENT AND FROST TREATMENT - An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (06-16-2011
20110168839DEVICE FOR CONNECTING AN AIR INLET WITH AN AIRCRAFT NACELLE ACTUATOR ASSEMBLY - An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.07-14-2011
20090283633INFILL PANEL OF A SUPPLY ARRANGEMENT IN A PASSENGER CABIN - A supply device in a passenger cabin, such as an aircraft passenger cabin, includes a first panel or “function panel” having one or more comfort elements, operating elements, visual display elements, and communication elements; and a second panel or an “infill panel”, which includes flexible supply channels. The panels are guided and lined up in a rail system of a PSC channel that is arranged in the direction of flight above a passenger seat row. The function panels are individually positionable in the PSC channel relative to the passenger seat row, wherein the infill panel synchronously follows a linear actuating movement of the function panel, and in this process automatically compensates for the distance dimension S11-19-2009
20090289146INTEGRATED ACOUSTIC DECOUPLING IN A HABITATION MODULE - According to an exemplary embodiment of the invention, a combined habitation module for the crew of an aircraft is provided, which habitation module comprises two monument units that are separated from each other by a gap such that acoustic decoupling of the two monument units from each other is provided. In this way noise propagation within the habitation module may be prevented to a large extent.11-26-2009
20120085861DEVICE FOR ACOUSTIC TREATMENT OF THE NOISE EMITTED BY A TURBOJET - The invention provides a device for acoustical treatment of the noise emitted by a bypass turbojet comprising a primary cowl having in an outer surface an inner annular acoustic treatment panel and a secondary cowl including in an inner surface an outer annular acoustic treatment panel arranged facing the inner panel. The inner and outer panels include respective central panel portions facing each other and extending axially over a common predetermined length, the length of the central panel portions lying in the range one-fifth to four-fifths of the total length of the panels, and the ratio between the acoustic resistances of the central panel portions being not less than 2.04-12-2012
20120032024WING-TO-BODY FAIRING WITH SPRAY-ON FOAM AND NOISE REDUCTION METHOD - A fairing includes a fairing body having a fairing interior and an interior surface and a spray-on insulation foam layer provided on the interior surface of the fairing body.02-09-2012
20120292441SYSTEM AND METHOD FOR REDUCING THE NOISE OF PUSHER TYPE AIRCRAFT PROPELLERS - A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method provide an airfoil-shaped flight surface with (i) a scoop configured to route boundary layer air and associated wake from said flight surface, and (ii) a suction device configured to provide a suction pressure, wherein the scoop routes boundary layer air from the flight surface to the suction device via an opening in the flight surface.11-22-2012
20110001004Landing Gear - An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains.01-06-2011
20120292440Mass flow increase at takeoff in supersonic airliner - In a supersonic aircraft, turbojet engine nacelles each containing two remote fans in the front half of the nacelle, for noise reduction at takeoff. During supersonic flight, a front wedge at the nacelle nose achieves external compression of intake air. The wedge is vertical, sending the airflow left and right inside the nacelle along its side walls. The two flows follow mirror image curved paths on their way to a turbojet, leaving unused space between them to house the fans in tandem. For takeoff, clutches connected to the turbojets's compressors are engaged. Driveshafts turn pinions against a gear on the same shaft as the remote fans. The fan output is discharged backward under the nacelle to produce thrust. The energy to turn the fans is taken from the turbojet cycle. The reduced exhaust jet velocity decreases its noise. Supercharging produces the extra power to turn the remote fans if multistage.11-22-2012
20120068012ARRANGEMENT AND AIRCRAFT OR SPACECRAFT - The present invention provides an arrangement, in particular for an aircraft or spacecraft, comprising an outer skin portion, the outside of which comes into contact with the atmosphere; a facing portion, which is arranged on the inside of the outer skin portion; a gap which is formed between the outer skin portion and the facing portion; and a device by means of which an airstream can be passed through the gap at a sufficient temperature to displace the dew point into the outer skin portion.03-22-2012
20120068011Active Aircraft Pylon Noise Control System - An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.03-22-2012
20100264264METHOD FOR PRODUCING AN AIRCRAFT WITH REDUCED ENVRIONMENTAL IMPACT AND THE AIRCRAFT THUS OBTAINED - A method for producing an aircraft with reduced environmental impact and the aircraft thus obtained.10-21-2010
20100148001AIRCRAFT CABIN PANEL WITH CORE RECESSES FOR ACOUSTIC ABSORPTION - An aircraft cabin panel for acoustic absorption in an interior space includes a core layer, a first cover layer and a second cover layer. The first cover layer includes a space-enclosing first surface, and the second cover layer is arranged opposite the first cover layer. The first cover layer is acoustically transparent, and the core layer includes a honeycomb core with a plurality of tubular or honeycomb-like cells that are open throughout the thickness of the honeycomb core. The honeycomb core on the face pointing towards the first cover layer extends parallel to the first cover layer so as to be continuously throughout, and on the face pointing towards the second cover layer comprises recesses which extend over several cells. Absorbers are accommodated in the recesses.06-17-2010
20100155529Landing gear with noise reduction fairing - An aircraft noise reduction apparatus is provided which includes an aircraft landing gear assembly and a noise reduction fairing 06-24-2010
20090314885SYSTEM, METHOD AND APPARATUS FOR FLUIDIC EFFECTORS FOR ENHANCED FLUID FLOW MIXING - A fluidic effector provides enhanced plume mixing for an aircraft engine. Air jet injectors are located on both the external and internal cowl surfaces and angled in opposite directions to induce large scale vortices in the exhaust plume. The vortices mix actuation air with the exhaust plume to produce ejector action. The plume mixes out quickly, thereby lowering jet noise and jet exhaust temperature. The injectors have orientations and injection rates that are adjustable to allow variable mixing rates for use at different flight and engine conditions.12-24-2009
20100252677AEROPLANE WITH IMPROVED ACOUSTIC COMFORT - An aircraft includes a cabin in which at least part of the space is demarcated by trim panels and the cabin is provided with a system for the active control of ambient noise. Each trim panel is either an active panel including actuators powered by the active noise control system or a passive panel without such actuators. In addition, the trim panels of the cabin of the one type, either active or passive, are mechanically interchangeable with a panel of the other type, either passive or active, respectively. Power supply wiring for active panels is installed in the aircraft, this wiring being capable of powering all active panels which could be installed, whether said active panels are actually installed or whether interchangeable passive panels are installed. Finally, a power supply system for the active panels is installed in the aircraft and connected to the power supply wiring of the active panels.10-07-2010
20100219288Deployable Flap Edge Fence - A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.09-02-2010
20110248117MULTILAYER BOARD FOR ACOUSTIC INSULATION - A multilayer board is provided for acoustic insulation and to a method for producing said board. In order to reduce sound emission and at the same time improve stability, a multilayer board for acoustic insulation is proposed that includes, but is not limited to a core sheet, a first covering layer and a second covering layer. At least one of the two covering layers is of a closed design. The core sheet is arranged between the first covering layer and the second covering layer and is firmly connected in a planar fashion to the covering layers. Furthermore, the core sheet comprises slits that extend within the core sheet in the direction of the core sheet thickness, which slits reduce the shear stiffness of the board and thus ensure an improved acoustic insulation effect. On both sides the core sheet comprises continuous edge zones, which extend parallel to the covering layers, in order to, together with the covering layers, ensure the best possible stability of the board. The invention in particular also relates to an aircraft with an interior lining formed by panels that comprise the multilayer boards according to the invention in order to provide acoustic insulation.10-13-2011
20100301161ACOUSTIC COATING FOR AN AIRCRAFT INCORPORATING A FROST TREATMENT SYSTEM BY JOULE EFFECT - The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (12-02-2010
20100133378ACOUSTIC PANEL HAVING A VARIABLE ACOUSTIC CHARACTERISTIC - An acoustic panel includes a reflective layer, at least one alveolar structure, and an acoustically resistive structure forming an aerodynamic surface of an aircraft on the surface of which at least one acoustic wave propagates along an axis of propagation (06-03-2010
20110079680Aircraft with tuned vibration absorber mounted on skin - An apparatus and method for attenuating noise and vibration in a propeller aircraft comprises a tuned vibration absorber adapted to be mounted to the skin of a fuselage of a propeller aircraft. The tuned vibration absorber may be tuned to the second harmonic of a blade passage frequency of a propeller of the aircraft. The tuned vibration absorber may be connectable to a separately formed mount, which can be mounted to the fuselage skin independently of the tuned vibration absorber. The apparatus may include a cover to prevent interference between the tuned vibration absorber and other components in the aircraft. The apparatus may be used in combination with other attenuation systems to attenuate noise and vibration over a broad range of frequencies.04-07-2011
20120145826HIGH-LIFT-DEVICE, WING, AND NOISE REDUCTION DEVICE FOR HIGH-LIFT-DEVICE - In a high-lift-device, a wing, and noise reduction device for a high-lift-device that are capable of reducing noise generated when a flap is extended, preventing deterioration of aerodynamics characteristic when retracting the flap, and preventing an increase in weight, a flap main body (06-14-2012
20100038476DEVICE THAT MAKES IT POSSIBLE TO IMPROVE THE EFFECTIVENESS OF THE ACOUSTIC TREATMENTS IN A PIPE OF AN AIRCRAFT POWER PLANT - A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe (02-18-2010
20090321559Aircraft noise reduction apparatus - The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear.12-31-2009
20100038475ICE PROTECTION SYSTEM FOR A MULTI-SEGMENT AIRCRAFT COMPONENT - An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.02-18-2010
20110068222PROPULSION UNIT FOR AN AIRCRAFT AND AIR INTAKE STRUCTURE FOR SUCH A UNIT - This propulsion unit for an aircraft comprises: a fan (03-24-2011
20100294883AERODYNAMIC SEAL FOR REDUCTION OF NOISE GENERATED ON AIRCRAFT CONTROL SURFACES - Flap side edge noise mechanisms have been addressed in a large number of studies during the last decades. A specific vortex system emanates from the flap side edge due to the static pressure difference between the upper and lower flap surfaces. Such pressure difference leads to a merging between the two vortex systems that are generated on the upper and lower edges of the flap side contour. The present invention intends to show the application of a perforated blade seal (11-25-2010
20100320316AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE - The invention relates to an air intake for an aircraft nacelle that comprises a shroud (12-23-2010
20100282900System for Reducing Aerodynamic Noise at a Supplementary Wing of an Aircraft - A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.11-11-2010
20110114787ACOUSTIC TREATMENT PANEL WITH INTEGRAL CONNECTING REINFORCEMENT - An acoustic treatment panel includes, from the inside to the outside, a reflective layer (05-19-2011
20090090812Insulation of an Aircraft Fuselage Structure - An insulating mat for the sound insulation of an aircraft fuselage structure that is composed of frames and stringers extending transverse to the frames, to a fastener means for fastening an insulating mat on an aircraft fuselage structure such that acoustic bridges are prevented. An insulating kit is also provided that comprises at least one insulating mat as well as at least one fastener. The insulating mat features a plurality of fastening clips that are fixed on a first surface of the insulating mat and laterally protrude over the border of the insulating mat.04-09-2009
20080237395BVI NOISE REDUCTION METHOD AND APPARATUS FOR HELICOPTER - The present method is characterized by providing the rotor blade with a tab 10-02-2008
20090078821LANDING GEAR - An aircraft noise-reduction apparatus (03-26-2009
20120012698AIRCRAFT COMPRISING AN INSULATION SYSTEM FOR THERMAL AND ACOUSTIC INSULATION - The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.01-19-2012
20110089290AIRPLANE CONFIGURATION - An aircraft configuration that may reduce the level of noise, infrared radiation, or combination thereof directed towards the ground from an aircraft in flight. An embodiment of an aircraft includes a fuselage, two forward swept wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. The leading edge of the wing may extend forward of the leading end of the engine, and the trailing edge of the aft deck may extend aft of the trailing end of the engine. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck. Engine types may vary, including but not limited to turbofans, prop-fans, and turbo-props. Main wings may be mounted above the longitudinal axis of the fuselage, and canards may likewise be mounted above or below the axis.04-21-2011
20120119023METHOD AND APPARATUS FOR REDUCING AIRCRAFT NOISE - An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface.05-17-2012
20120119024INSULATION ARRANGEMENT IN AN AIRCRAFT - An insulation arrangement with a holding device that comprises a collar forms an overlapping region between a second insulating package and the collar such that incidental condensation water on a first insulation package drains to the second insulating package along the collar under the influence of the gravitational force and from there into a bilge of the aircraft equipped with the insulation arrangement on a waterproof cover film of the second insulating package. This prevents condensation water from dripping into a passenger cabin.05-17-2012
20100288876BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element (11-18-2010
20110180660AIRCRAFT HAVING A LAMBDA-BOX WING CONFIGURATION - Aircraft having a lambda-box wing configuration, comprising a fuselage (07-28-2011
20120211599FLOW-MODIFYING FORMATION FOR AIRCRAFT WING - An aircraft wing has an engine attachment position at which a gas turbine engine is attached beneath the wing, in use the engine ejecting a propulsive gas jet with a jet shear layer being formed between the gas jet and the surrounding air. The aircraft wing further has one or more elongate, flow-modifying formations protruding from the underside of the wing. The length direction of the or each formation is along the fore and aft direction of the wing with the trailing edge of the formation being rearward of the trailing edge of the wing. The flow-modifying formations can be arranged such that they interact with the jet shear layer to reduce noise generated by the interaction of the jet shear layer and the wing. They can also be arranged to block, attenuate and/or to scatter the noise reflected by the wing.08-23-2012
20100012778Torque link set - An aircraft landing gear (01-21-2010
20100012777Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.01-21-2010
20120256048Vibration Isolation System - A vibration isolation system for attenuating vibration energy between two aircraft structures, such as between the aircraft's fuselage and interior cabin. The vibration isolation system includes a first isolator attached to the first structure, a second isolator attached to the second structure, and an intermediate mass attached between the first and second isolators. The intermediate mass may be electrical cables, wiring bundles, a cable holder, or other component disposed between the two structures. Cable holder intermediate masses can be fabricated from an electrically conductive material to provide electromagnetic interference shielding for cables disposed therein. Multiple vibration isolation systems can be disposed between the fuselage and interior cabin to provide a less noisy cabin. Additional noise and vibration suppressors, such as skin damping material and acoustic blankets, also can be disposed between the fuselage and interior cabin to further reduce noise in the interior cabin.10-11-2012
20120267476ACOUSTICALLY OPTIMIZED AIR CONDITIONING COMPONENTS - Systems and methods for sound damping in air conditioning systems in an aircraft is provided. In one embodiment, an air conditioning conduit can comprise a sound-damping wall that at least partially encloses a continuous hollow space for guiding the air. The wall comprises a multilayer design with a core layer and at least one first cover layer. The core layer comprises a sound-absorbing open-pore core material so that the wall shows an acoustic effect. The first cover layer is airtight, is arranged on the external surface of the core layer, and is two-dimensionally connected to the core layer. The two-dimensional connection between the core layer and the first cover layer causes a composite effect in such a manner that the wall is self-supporting and has a structural function in order to be able to transfer mechanically-occurring loads to structural parts of the aircraft.10-25-2012
20120267475ACOUSTIC SEAL FOR AIRCRAFT - An acoustic seal device is placed around the periphery of aircraft doors for reducing reducing wind noises transmitted into the aircraft cabin by the door gaps without adding additional weight to the aircraft. The acoustic seal includes a pre-shaped body made of a soundproofing material. The pre-shaped body is adapted to be secured to a door opening and has a shape that matches the shape of the door opening.10-25-2012
20110226897Launch vehicle fairing and construction - Light-weight acoustic dampening launch vehicle fairing structures having high strength and stiffness and capable of filling to provide high mass density and rapidly unloaded at a predetermined time following launch, and methods of making them are provided. The panels include a monolithic body comprised of fibrous reinforcement material in a polymeric binder and comprise longitudinal chambers extending from the length of body. Fluid passage means are provided at both the top and bottom of the monolithic body and interconnected by the longitudinal chambers for filling and emptying said chambers with a fluid.09-22-2011
20120091270AIRCRAFT CONFIGURATION - An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stabilizers outboard of the outermost engine. Noise shifting means are provided such as, for each nacelle, primary chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer, a long duct full flow mixer, or a combination thereof to provide a shift in spectrum distribution of jet exhaust noise from lower to higher frequency. Variable geometry chevrons may be used with increased immersion to provide such a shift just during noise-restricted portions of an aircraft flight profile. The aircraft aerodynamic structural surfaces serve as noise shielding barriers that more effectively block or redirect the frequency shifted noise up and away from communities.04-19-2012
20100181420COATING FOR ACOUSTIC TREATMENT THAT INTEGRATES THE FUNCTION OF HOT-AIR TREATMENT OF FROST - The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (07-22-2010
20130009002TURBOSHAFT ENGINE SUPPORTING PYLON COVERED WITH A POROUS MATERIAL AND TURBOSHAFT ENGINE/PYLON ASSEMBLY - A turboshaft engine supporting pylon covered with a porous material and a turboshaft engine/pylon assembly. The pylon supports a turboshaft engine on an aircraft, and includes an outer surface covered at least partially with a porous material to reduce amplitude of acoustic waves leaving the turboshaft engine. The assembly includes a turboshaft engine and a pylon, in which the pylon extends longitudinally from upstream to downstream and includes an upper part for securing to the aircraft, a lower part for securing to the turboshaft engine, and an absorption part extending in an exhaust stream from the turboshaft engine and including an internal absorption part extending inside the turboshaft engine and an external absorption part extending downstream of the turboshaft engine. The outer surface of the upstream end of the external absorption part of the pylon is covered with a porous material to limit noise formation downstream of the engine.01-10-2013
20130020434Condensed Water Decreasing Insulation Package For Thermal And Acoustic Insulation Of A Vehicle Cabin - An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin.01-24-2013
20130175392QUIET LANDING ATTITUDE MODIFIER FOR AIRPLANE - The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting.07-11-2013
20120256049Systems and Methods for Attenuation of Noise and Wakes Produced by Aircraft - Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise.10-11-2012
20100294882AIRCRAFT LEADING EDGE - An aircraft leading edge, such as, for example, an air intake (11-25-2010
20090256027Aerodynamic Noise Reducing Method (Variants) and Low-Noise Structural Element for Operating in a Fluid Medium Stream - The invention relates to aerodynamic. The inventive method for reducing the aerodynamic noise generated by separation a medium stream streaming around a structural element surface during the relative motion thereof consists in forming a low-curvature area consisting of at least one continuous section on at least one part of the structural element surface operating beyond the medium stream separation line and in orienting said structural element with respect to the medium stream in such a way that a normal line direction with a structural element surface is close to or coincides with the vector velocity direction of the medium stream on the entire or major part of the area surface. According to the second variant of the method the low-curvature is not formed at the production stage but is determined on the structural element surface of an existing structure using the features of the shape thereof. A low-noise structural element produced by the inventive method is also disclosed. The device also can be developed in such a way that it makes it possible to optimize the use thereof in particular application cases. The aim of the invention is to reduce the aerodynamic noise without deteriorating other aerodynamic characteristics of a structure.10-15-2009
20120273611EXHAUST SILENCER WITH BAFFLES - An exhaust silencer assembly includes an exhaust duct and an exhaust silencer. The exhaust silencer is disposed about the exhaust duct and has a plurality of solid baffles and at least one perforated baffle The exhaust silencer assembly is disposed downstream of an auxiliary power unit and at least partially attenuates the downstream noise of the combustion gases that result from operation of the auxiliary power unit. In one embodiment, at least one of the plurality of solid baffles is disposed to extend axially between generally radially extending solid baffles, perforated baffle(s), or partially perforated baffles. The axially extending solid baffle allows for cavity depth variation in the silencer to optimize tuning of particular frequencies from the auxiliary power unit.11-01-2012
20110303786SILENCER FOR AN AUXILIARY POWER UNIT OF AN AIRCRAFT - A silencer for an auxiliary power unit of an aircraft comprises an inlet, an outlet, a housing and a flow channel with a porous wall material that is arranged in the housing. An intermediate space is formed between the housing and the flow channel and divided into outer cells that are arranged around the flow channel by means of one or more partitions. This makes it possible to realize a very compact silencer with very good sound insulation properties. The sound dampening can be additionally improved by dividing the outer cells into outer regions and inner regions, by adapting the shape of the silencer to a tail section of an aircraft and by arranging an annular channel on the outlet.12-15-2011
20110315819Supersonic Aircraft with Spike for Controlling and Reducing Sonic Boom - Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.12-29-2011
20130193268BLUFF BODY NOISE CONTROL - An aircraft noise-reduction apparatus comprise a flow-facing element (08-01-2013
20090206198AIRCRAFT ENGINE STRUCTURE-MOUNTED AIM-POINT BIASING INFRARED COUNTERMEASURE APPARATUS AND METHOD - A thermal radiation-generating decoy mounted adjacent an aircraft engine structure, such as an engine nacelle, includes a heat source inside of an aerodynamic enclosure with a mounting interface to attach the enclosure to the engine structure. The decoy can further be located at the lower extreme of and adjacent the forward-most portion of the engine nacelle in order to attract an infrared-seeking threat to the vicinity of the fan containment portion of the engine nacelle. The decoy can be designed to have a thermal signature that mimics a scaled overall aircraft thermal signature. In addition, the decoy can include a fuse shield adjacent the enclosure to detonate a threat in the case that the threat approach trajectory is imprecise and the threat bypasses the enclosure within an aspect of the fuse shield as viewed from the approach direction of the threat.08-20-2009
20100163673METHOD AND APPARATUS FOR FAST DEPLOYING AND RETRIEVING OF TOWED BODIES - In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position.07-01-2010
20130062464TOWED SENSOR ARRAY MANEUVERING SYSTEM AND METHODS - A towed sensor array maneuvering system and methods are disclosed. A towed airborne vehicle comprising a sensor array is actively maneuvered via a plurality of surfaces coupled thereto. The surfaces are controlled such that a desired path is tracked based on and as a function of desired tracking parameters.03-14-2013
20090314886DEPLOYMENT OF TELESCOPING AIRCRAFT STRUCTURES BY DROGUE PARACHUTE RISER TENSION - A system for deploying a deployable structure in an aircraft, comprising a drogue parachute, at least one deployable structure, a riser line attached to the drogue parachute and the at least one deployable structure, wherein when the drogue parachute is deployed, a tension is applied to the riser line, and a parachute deployment system, wherein the parachute deployment system is configured to utilize the applied tension to deploy the at least one deployable structure.12-24-2009
20110278393AERODYNAMICALLY STABILIZED INSTRUMENT PLATFORM - A suspension apparatus for suspending instrumentation from an airborne platform may include a generally longitudinal boom having a payload end and a tail end. Yaw and pitch stabilizers may be disposed at the tail end of the boom. A mast that may be selectively translatable on the boom may connect the boom to a tether line of the airborne platform. The payload may be attached to the payload end of the boom. The mast may be positioned axially along the boom at the center of gravity of the combination of the payload, boom, pitch stabilizer, and yaw stabilizer.11-17-2011
20110139928AUTOGYRO AIR VEHICLE - An unmanned, towable aerovehicle is described and includes a container or frame to hold or support cargo, at least one and, in some examples, a plurality of autogyro assemblies connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container or frame includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. In an example, the electrical motor does not have enough power to sustain flight of the vehicle. The aerovehicle can further include plurality of autogyro assemblies to assist in flight. The aerovehicle can include surfaces that provide lift or control to assist in the flight profile of the aerovehicle.06-16-2011
20090127387Method for recovering a relatively slower moving vehicle - A method whereby a relatively faster-moving vessel recovers a relatively-slower moving vehicle is disclosed.05-21-2009
20100276537SYSTEM AND METHODS FOR AIRBORNE LAUNCH AND RECOVERY OF AIRCRAFT - A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to secure the aircraft to the flexible tether. In certain embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Alternatively, the aircraft translates forward and rearward as the flexible tether taken up and let out from the mother ship. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether.11-04-2010
20090065639Separate Communication Line for Towed Body - The present invention relates to a system for connecting an aircraft to a towed body, which comprises: (a) a reduced towing cable comprising tension filaments to provide the tensional force required for towing the body; (b) a signal cable, separate from said reduced towing cable, for conveying signals between the aircraft and the towed body, said signal cable comprises one or more optical fibers; and (c) conductive wires either within said towing cable or within said signal cable for providing electrical path between the aircraft and the towed body.03-12-2009
20100038477SYSTEM AND METHODS FOR AIRBORNE LAUNCH AND RECOVERY OF AIRCRAFT - A system and methods for airborne launch and recovery of aircraft. In one embodiment the system comprises a flexible tether configured to be towed behind an airborne mother ship. A drag device is secured to a distal end of the flexible tether to generate drag and maintain tension in the flexible tether. A reel associated with the mother ship anchors a proximal portion of the flexible tether and selectively lets out and takes up the flexible tether to adjust a length of the flexible tether. A capture mechanism associated with the aircraft engages the flexible tether to enable the aircraft to translate along the flexible tether. In embodiments of the present methods, a flexible tether is deployed from an airborne mother ship. An aircraft translates forward and rearward along the flexible tether. Prior to launch, the weight of the aircraft is transferred from the flexible tether to the wings. During recovery, the weight of the aircraft is transferred from the wings to the flexible tether.02-18-2010
20110068223Aircraft Decoy Arrangement - Aircraft decoy arrangement and method for generating a decoy signal from an aircraft having an isolated decoy. An aircraft receiver detects a threat signal from a threat source targeting the aircraft. An aircraft signal processor produces a decoy relay signal based on the threat signal, where the decoy relay signal frequency is significantly lower than the threat signal frequency and is slowly attenuated through air, the signal processor calibrating the decoy relay signal in accordance with a received test signal to compensate for inaccuracies. An aircraft transmitter transmits the decoy relay signal and an optional reference signal to the decoy, where it is received by a decoy receiver, converted back to a decoy signal by a decoy frequency converter, and transmitted by a decoy transmitter, causing the threat source to detect the decoy signal and lock onto the decoy rather than the aircraft.03-24-2011
20110174922UNGUIDED MISSILE AND PROJECTILE DEFENSE SHIELD SUPPORTED BY TETHERED BALLOONS - In this invention, there is provided a method and device for shielding and deflecting unguided missiles, mortars and other projectiles and ordnance. A plurality of lighter-than-air balloons are tethered from a plurality of ground anchors so that the balloons are positioned spaced apart, adjacent to, along and buoyed above the border to be defended between the launch area and the target area. A defense shield is suspended from the plurality of tethered lighter-than-air balloons, extending generally vertically covering a range of heights for engaging and deflecting missiles launched along the expected trajectories.07-21-2011
20100288877DECOY PROTECTION SYSTEM FOR AIRCRAFT AND METHOD OF PROTECTION - The current invention is inclusive of a decoy protection system and method of protecting jet aircraft from shoulder fired missiles comprising while such aircraft is in a flight envelope where it is susceptible to being hit by a such a missile, by employing a decoy means towed by aircraft at a distance away from the aircraft whereby the decoy means is located sufficiently remote away from any part of said aircraft that a missile strike on the decoy mean will not normally damage the aircraft, supplying said decoy means with jet fuel from said aircraft and burning said jet fuel in the decoy means to create a high intensity IR signature in the decoy means sufficient to divert shoulder fired missiles from said aircraft to said decoy means.11-18-2010
20080217474Method and apparatus for fast deploying and retrieving of towed bodies - In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position.09-11-2008
20110272522AIRBORNE TIME DOMAIN ELECTROMAGNETIC TRANSMITTER COIL SYSTEM AND APPRATUS - A tow assembly for an airborne electromagnetic surveying system, including: a transmitter coil frame supporting a transmitter coil, the transmitter coil frame being formed from a plurality of serially connected frame sections forming a loop, the transmitter coil frame having rotating joints at a plurality of locations about a circumference thereof enabling the transmitter coil frame to at least partially bend at the rotating joints; and a suspension assembly for towing the transmitter coil frame behind an aircraft, the suspension assembly being attached to the circumference of the transmitter coil frame at spaced apart locations.11-10-2011

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