An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.
A vehicle having an aerodynamic splitter for the front of a vehicle is provided. The splitter includes a splitter panel which has a top surface adapted to be mounted to a front fascia of a vehicle. The top surface is contoured and offset from the front fascia in order to define an airflow opening between the front fascia and the splitter panel. The airflow opening directs air under the vehicle therethrough in order to create a down force on the vehicle
An aerodynamic projectile is provided having a shell with an aerodynamic structure and a controlled center of gravity, and which exhibits improved aerodynamics and resulting accuracy, and which is suitable for less lethal uses. The projectile shell has a closed front cavity housing a payload, such as a marking agent, therein. The projectile shell also has an open rear portion to provide access to the open rear cavity, and to decrease the weight of the projectile and appropriately locate the center of gravity. The projectile shell also includes a plurality of fins on a sidewall member to enhance the accuracy of the projectile.
Multiple projections are provided at a flow-change portion, which corresponds to such a portion of a wall surface of an A/C casing, at which velocity gradient of air current becomes larger in an area adjacent to the wall surface, in order to decrease aerodynamic sound generated by disturbed air current.
An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump.
Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals.
A gas turbine engine system includes a fan section, a low pressure compressor section downstream of the fan section, a first engine core downstream from the low pressure compressor section, a second engine core downstream from the low pressure compressor section, and a flowpath control mechanism configured to selectively restrict fluid flow through the second engine core. The first engine core includes a first engine core compressor section, a first engine core combustor downstream of the first engine core compressor section, and a first engine core turbine section downstream of the first engine core combustor. The second engine core includes a second engine core compressor section, a second engine core combustor downstream of the second engine core compressor section, and a second engine core turbine section downstream of the second engine core combustor.
Aerospace ground maneuver light, comprises a reflector (14), the reflector (14) defining a light exit plane (18), an LED light source (26) arranged outside of the area defined by the reflector (14) and its light exit plane (18), and a mounting bar (22) which has a longitudinal extension and at which the LED light source (26) is mounted. The mounting bar (22) extends across the reflector (14) and is spaced apart from the light exit plane (18) of the reflector (14) and comprises a mounting side (24) facing towards the reflector (14) and its light exit plane (18), with the LED light source (26) arranged on the mounting side (24) for emitting light towards the reflector (14).
An aerospace-ground integration testbed may include a truth data scheme, a common sensor adaptor, a common sensor framework, a visualization scheme and a communications scheme. The truth data scheme may generate truth data configured to provide data of at least one of threats, terrain, targets and offensive and defensive systems. The common sensor adaptor may provide sensed data generated from at least the truth data. The common sensor framework may provide modeled sensed data generated from at least the truth data utilizing sensor models. The visualization scheme may generate visual data to be displayed from the sensed data and the modeled sensed data. The communications scheme may provide communication and testbed messaging infrastructure between the truth data scheme, the common sensor adaptor, the common sensor framework, and the visualization scheme.
An aircraft capable of hovering, and characterized by having at least one sensor, which has a plane sweep region and is designed to acquire, when the aircraft is manoeuvring, values of respective distances between first points on an obstacle within the plane sweep region, and a second point on the aircraft; and a control unit designed to generate an alarm signal when at least one of the first points lies within a safety region containing the second point on the 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 (5A) associated with the structural element (2) is retractable and capable of occupying at least one position located between the following two end positions: a deployed position, in which the net is placed in a turbulence area (T), and a retracted position, in which said net (5A) is at least partially outside said turbulence area (T).
Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.
An aircraft interior power converter comprises electronic circuitry that includes a primary power converter operative to convert an AC input power supply to a primary DC output power supply, a regulator for at least one of the DC output voltages required, the regulator being operative to receive the primary DC output power supply and generate a DC input power supply at the voltage required for a particular DC outlet connected to that regulator. An output protection circuit is provided for each DC outlet and is operative to receive a DC input voltage. Each output protection circuit comprises a comparator circuit that generates a load signal indicative of the electrical load being taken by that DC outlet, compares that load signal against a predetermined load limit, and generates an output control signal to disconnect the DC input voltage from the DC outlet if the load signal exceeds the predetermined load limit.
A method, apparatus and software are disclosed for enabling asymmetric deployment or retraction of aircraft landing gear.
An aircraft taxi drive system includes a motor that is configured to transfer power to an aircraft wheel via a drive chain, such that the motor rotates the aircraft wheel via the drive chain. In some examples, the drive chain is movable between first and second positions. In the first position, the drive chain, such as an exterior surface of the drive chain, is engaged with a driven sprocket that is mechanically connected to an aircraft wheel. In the second position, the drive chain is disengaged from the driven sprocket.
Apparatuses and methods for joining composite members and other structural members in aircraft wings and other structures. An aircraft wing box structure configured in accordance with one embodiment of the invention includes a first composite member having a first surface portion positioned at an angle relative to a second surface portion of a second composite member. The wing box structure of this embodiment further includes at least one metallic joining member having an upstanding leg portion extending from a base portion. The base portion of the joining member is bonded to the first surface portion of the first composite member with a first portion of adhesive, and the upstanding leg portion of the metallic joining member is bonded to the second surface portion of the second composite member with a second portion of adhesive.
Automated positioning and alignment methods and systems for aircraft structures use anthropomorphous robots with six degrees of freedom to carry the aero structure parts during the positioning and alignment. The parts and structures (if any) supporting the parts are treated as robot tools.
Automatic estimation process and device for a flight parameter vector in an aircraft, as well as detection methods and assemblies for a failure affecting such a vector. The detection device (1) comprises means (5) for estimating, on an observation window, a coefficient vector allowing to determine a linear relationship between the searched flight parameter vector and explanatory values, by implementing a PLS regression, and means (5) to use such a coefficient vector so as to calculate, thru a linear modeling, an estimated value of said flight parameter vector.
A self-managing system that uses autonomy and autonomicity is provided with the self-* property of autopoiesis (self-creation). In the event of an agent in the system self-destructing, autopoiesis auto-generates a replacement. A self-esteem reward scheme is also provided and can be used for autonomic agents, based on their performance and trust. Art agent with greater self-esteem may clone at a greater rate compared to the rate of an agent with lower self-esteem. A self-managing system is provided for a high volume of distributed autonomic/self-managing mobile agents, and autonomic adhesion is used to attract similar agents together or to repel dissimilar agents from an event horizon. An apoptotic system is also provided that accords an \"expiry date\" to data and digital objects, for example, that are available on the internet, which finds usefulness not only in general but also for controlling the loaning and use of space scientific data.
An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed.
There is provided a cockpit window of an aircraft and the aircraft in which an electromagnetic shield film for preventing electromagnetic noise can be reliably and easily provided at low cost. An electromagnetic shield film is provided to a window part, and a conductive film is provided between the electromagnetic shield film and an outer retainer made of a conductive material. The conductive film is connected to the electromagnetic shield film via a connecting member is provided so as to be led to an outer perimeter side of the window part along an outer perimeter part of the window part, and is electrically connected to the outer retainer. With this configuration, a film made of a conductive material is formed without a gap at a joint portion between the window part and the outer retainer. Also, the conductive film is assumed to have flexibility.
A method of treating a hole in a metallic component includes the following steps in sequence: forming an hole having a first diameter in the component; expanding the hole to a second diameter using a cold expansion process, so as to induce residual compressive stresses in the material surrounding the hole; shot peening the hole; and final machining the hole to a finished diameter.
A composite structure for aerospace applications includes a structural member having multiple composite layers providing a longitudinally extending cavity. A conveyance element is arranged between and integral with the layers. In one example, the structural member provides a gas turbine engine duct or an airframe component. A composite structural assembly is manufactured by providing a first composite layer on a form that corresponds to a cavity. A second form, which may be a conveyance element in one example, is positioned along the first layer. A second composite layer is laid onto the second form and the first composite layer to provide a composite structural member with an integrated conveyance element.
This invention relates to a control system for an aircraft consisting of at least two active inceptor units and at least one coupling means, wherein the coupling means generates or influences at least one setpoint for the control of at least one of the active inceptor units, wherein the generated setpoint corresponds to a movement setpoint for a movement controller.
A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system.
Detecting inconsistencies proximate a panel splice joint involves trimming a portion of a first panel overlapping a second panel to expose a previously overlapped region of the second panel. The previously overlapped region of the second panel may be inspected to detect any inconsistencies present thereon after trimming the portion.
A device for characterizing the nature of an aerodynamic stream along a wall, the device including multiple temperature-sensitive optical nodes of Bragg grating type distributed along an optical fiber, and means for determining the variations in speed of the aerodynamic stream. The nodes are distributed along a fiber placed substantially following the route of a streamline, and processing means are devised so as to differentiate the temporal and spatial characteristics of the signals of thermal flowrate among the nodes.
A device for locating a first aerospace component relative to a second aerospace component, comprising a bladder with a flexible membrane which defines a fluid receiving space such that, when a hardenable hydraulic fluid is injected into the bladder, said membrane is urged to deform into abutment with said first and second aerospace components to locate said components relative to each other when the hydraulic fluid hardens.
In the field of aviation, a device for limiting aerodynamic noise from a deployed aircraft undercarriage during landing and/or takeoff. The device comprises two end plates (4a, 4b) for closing respective ends (2a, 2b) of a hollow pin (1) of the undercarriage, such as a hinge pin between two rods of the undercarriage, together with at least one tie (6) for engaging inside the hollow pin (1) to connect the two end plates (4a, 4b) together so as to hold them pressed against the ends (2a, 2b) of the pin (1).
A device for repairing a casing holder of an aeronautical engine extending radially relative to the engine rotational axis and including a plurality of lips, each having a hole drilled therein and evenly distributed on the circumference of the holder. The device includes at least one reinforcement holder that can be attached to clean lips of the case holder via through-holes or blind-holes, the reinforcement holder having two orthogonal planes of symmetry. The device further includes a reconditioning holder mounted on the reinforcement holder via a first part using attachment means positioned in one of the planes of symmetry of the reinforcement holder.
Flight management systems can behave erratically when the distance measurements on which they are based are subject to value jumps because they liken these value jumps to movements of the aircraft performed at speeds exceeding the performance levels of the aircraft for which they were designed. To avoid this, the proposed flight management system uses a filter to spread the distance value jumps in time, over periods of the order of those needed for the aircraft to come through the distance differences that they represent. This filter replaces a value jump with a ramp making up the difference and corresponding to a movement that remains within the performance scope of the aircraft.
A duplex coating scheme and associated method of formation, which includes a siloxane based soft coating and a plasma based SiOxCy hard coating used in combination to improve the durability of acrylic substrates used in aircraft window applications.
The use of dynamic collision avoidance parameters in connection with automatic dependent surveillance, broadcast, as well as for other purposes in systems and methods may assist collision avoidance and/or advisory systems in properly identifying intruders for reporting to pilots. For example, a method can include monitoring for a triggering event with respect to at least one of geographic coordinates and a flight path of an aircraft. The method can also include detecting the triggering event. The method can further include altering at least one characteristic of at least one of a traffic alerting system and an advisory system based on detecting the triggering event.
An elbow bracket for cables or pipes, supported by a structure of an aeronautical device, in which a reinforcing rib of the elbowed main plate is not assembled with the elbowed main plate by welding but by tightening following a twisting of end-pieces traversing slots of the main plate and causing an outer face of the plate to be trapped against an upper face of oblong slits partially cutting into the end-pieces. The support is faster to construct, and has sufficient resistance.
An electric and hybrid Vertical-Take Off and Landing (\"VTOL\") aircraft is disclosed comprising a plurality of small Electric Ducted Fans (\"EDFs\") of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions.
An electronic circuit, and a system including such a circuit, for determining a datum representative of a parameter of air surrounding an aircraft, including: a mechanism receiving, from a plurality of sources, a plurality of respective measurement data representative of a measured value of the parameter; a mechanism determining the datum representative of the parameter based on the measurement data; and a mechanism transmitting the datum representative of the parameter to a computer associated with an aircraft engine.
Embodiments of the present invention relate to a system for monitoring the characteristics of key components of aeronautical machines (e.g., airplanes, helicopters, etc.), processing obtained data, and delivering prognostic health indicators to improve machine performance and detect early warning signs of failure. In one embodiment, a method of maintaining prognostic health management accuracy of an aeronautic system comprises providing a control module and a sensor pod having a plurality of sensors, and physically positioning the plurality of sensors on a mechanical component of an aircraft; obtaining operational data from the sensors while the aircraft is operating in a native environment; transmitting operational data to the control module and determine real-time system performance characteristics; processing real-time system performance characteristics against a set of historical records containing past system performance characteristics and generating predictive indicators for forecasting remaining component lifetime and future component failures; and providing predictive indicators on an indicator means.
A system and method for analyzing a risk of extended operations (ETOPS) dual independent engine in-flight shutdown (IFSD) using an ETOPS IFSD risk calculation means is disclosed. A two-engine aircraft/engine combination performance data set is provided to obtain flight specific data, and a user input variable array is also provided. Flight times are calculated based on the flight specific data and the user input variable array. Dual independent engine shutdown total thrust loss probability values for various phases of an ETOPS flight are calculated based on the user input variable array, the flight specific data, and the flight times. A calculated risk of dual independent engine in-flight shutdown on the ETOPS flight is calculated based on a sum of the dual independent engine shutdown total thrust loss probability values.
A method for facilitating remote storage of preflight documentation for a helicopter air ambulance includes filling out a preflight documentation form for a helicopter air ambulance with a specially configured pen, the preflight documentation form including tiny dots printed thereon, and the specially configured pen being configured to electronically record information associated with marks made on the preflight documentation form; electronically communicating the information associated with marks made on the preflight documentation form, together with an identification of the specially configured pen, to a remote server; and generating, at the remote server, an electronic copy of the preflight documentation form including markings or text representative of the marks made on the preflight documentation form. The steps of filling out a preflight documentation form and electronically communicating information occur prior to takeoff of the helicopter air ambulance.
A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.
A fluid actuator for influencing the flow along a flow surface by ejecting a fluid flowing through the fluid actuator is described. The fluid actuator has at least two outlet lines with outlet openings at the respective ends thereof, and a feed line connected to the outlet lines for feeding fluid at a supply pressure, a flow direction diverting device into which the feed line opens and out of which the outlet lines open, and an adjusting device coupled to the flow direction diverting device to control the latter. The adjusting device is configured so the fluid is conducted successively in a cyclic sequence into each of the outlet lines. A discharge device for discharging a fluid out of a flow body, and a flow body having a multiplicity of discharge openings and a discharge device of said type are also described.
A thermoelectric module and methods for making and applying same provide an integrated, layered structure comprising first and second, thermally conductive, surface volumes, each in thermal communication with a separate respective first and second electrically conductive patterned trace layers, and an array of n-type and p-type semiconducting elements embedded in amorphous silica dielectric and electrically connected between the first and second patterned trace layers forming a thermoelectric circuit.
The present invention provides a fuselage arrangement for an aircraft or spacecraft, comprising: a skin portion which consists substantially of fibre composite material and/or of a fibre-composite/metal mixed material; a metal floor structure which is mounted on the skin portion; and a plurality of electrical system components which are interconnected in an electrically conductive manner by means of the floor structure.
A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one brace which is at least one of a longitudinal and a transverse brace is disposed so as to form at least one of a longitudinal seam and a transverse seam between the at least one double shell skin panel and the at least one monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flange that are disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the at least one monolithic skin panel to the at least one double shell skin panel.
A gas seal for aerospace engines has a stationary seal housing, a rotating seal plate mounted on the engine drive shaft and a carbon ring seal movably supported in the housing with a face which mates with the face of the seal plate to create a gas seal therebetween. A plurality of flexible pins have first ends supported on the housing and second ends slidably connected with the carbon ring seal to permit the latter to shift axially. A plurality of compression springs bias the two seal faces together. The housing has a first twist lock which selectively engages a second twist lock on the carbon ring seal to movably retain the latter in the housing. The second ends of the spring pins resiliently deflect during mutual rotation of the carbon ring seal and the housing to facilitate engagement and disengagement of the first and second twist locks.
A glass composition including SiO.sub.2 in an amount from 60.0 to 73.01% by weight, Al.sub.2O.sub.3 in an amount from about 13.0 to about 26.0% by weight, MgO in an amount from about 5.0 to about 12.75% by weight, CaO in an amount from about 3.25 to about 4.0% by weight, Li.sub.2O in an amount from about 3.25 to about 4.0% by weight, and Na.sub.2O in an amount from 0.0 to about 0.75% by weight is provided. Glass fibers formed from the inventive composition may be used in applications that require high strength, high stiffness, and low weight. Such applications include, but are not limited to, woven fabrics for use in forming wind blades, armor plating, and aerospace structures.
Golf balls include: (a) a golf ball body having a first set of construction specifications and a first dimple pattern formed on an outer surface of the golf ball body; and (b) a coating applied to the outer surface of the golf ball body to thereby produce a coated golf ball body having an exterior surface. At least one of the outer surface of the golf ball body and the coating includes a plurality of surface roughening particles to provide increased micro surface roughness as compared to golf balls having the same set of construction specifications and the same dimple pattern but without the micro surface roughening particles. The micro surface roughening affects the aerodynamic properties of the ball.
A golf club head includes a body member having a ball striking face, a crown, a toe, a heel, a sole, and a skirt extending between the crown and the sole and between the toe and the heel. The club head includes a drag-reducing structure that may include one or both of a continuous groove extending from a front portion to a rear edge of the toe, and along an entire length of the skirt, and a substantially V-shaped recess formed in the sole and having a vertex positioned proximate the ball striking face and the heel and away from the skirt and the toe, and a pair of legs extending to a point proximate the toe and away from the ball striking face, and curving toward the skirt and away from the ball striking face.
A system for converting audible air traffic control instructions for pilots operating from an air facility to textual format. The system may comprise a processor connected to a jack of the standard pilot headset and a separate portable display screen connected to the processor. The processor may have a language converting functionality which can recognize traffic control nomenclature and display messages accordingly. Displayed text may be limited to information intended for a specific aircraft. The display may show hazardous discrepancies between authorized altitudes and headings and actual altitudes and headings. The display may be capable of correction by the user, and may utilize Global Positioning System (GPS) to obtain appropriate corrections. The system may date and time stamp communications and hold the same in memory. The system may have computer style user functions such as scrollability and operating prompts.
A sensor for monitoring a plant population in front of a harvester and a transfer process of the crop from the harvester to a transport vehicle is arranged on an unmanned aircraft. The aircraft moves in the vicinity of the harvester in the harvesting mode and communicates in a wireless fashion with a control unit that controls an actuator for influencing an operating parameter of the harvester and/or the transport vehicle (in real time based on signals of the sensor in the harvesting mode.
A heat exchanger is provided in which heat exchanger shells are formed by electro forming about a mandrel. The shells are attached and joined to provide a heat exchanger module. As the shells are not press formed problems with respect to material elongation to achieve deep grooves in the shells are potentially avoided and shells can be created with more desirable thickness to achieve more efficient heat exchange. Furthermore, reduced shell thickness will also reduce weight and therefore improve the acceptability of heat exchangers in particular applications such as those associated with aerospace and automotive sports.
A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.
Provided is a high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other. In the tilt rotor aircraft having nacelles in which rotors are mounted in left and right main wings and configured so that the nacelles rotate according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight, each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle.
An interface system may be used for connecting a mother board with a peripheral device board. The interface system may include a mother interface and a daughter interface. The mother interface may establish a connection portal for the mother board, and the daughter interface may establish a connection portal for the peripheral device board. The interface system may be equipped with a socket with multi-contact surface for providing high speed, high performance, and low noise data transmission. The interface system may be ruggedized with various stabilizing mechanisms, such that it may deliver consistent and reliable performance under harsh military and/oraerospace conditions.
The present invention provides an Al--Zn--Mg--Cu casting alloy that provides high strength for automotive and aerospace applications and optimized stress corrosion cracking resistance in highly corrosive and tensile environments. The inventive alloy composition includes about 3.5 wt. % to about 5.5 wt. % Zn; about 1.0 wt. % to about 3.0 wt. % Mg; about 0.5 wt. % to about 1.2 wt. % Cu; less than about 1.0 wt. % Si; less than about 0.30 wt. % Mn; less than about 0.30 wt. % Fe; and a balance of Al and incidental impurities.
The invention relates to a treated HPPE yarn characterized in that the treated HPPE yarn comprises: a porous polyolefin layer that adheres to a surface of a HPPE yarn and covers at least partly the surface of the HPPE yarn; a composition comprising an active agent and which composition is at least partially absorbed within the porous polyolefin layer. The invention further relates to an article comprising the treated HPPE yarn, a device comprising the treated HPPE yarn or the article. The invention also relates to a process for preparing the treated HPPE yarn or treated HPPE yarn structure or treated HPPE yarn configuration and use of the treated HPPE yarn or an article or a device comprising the treated HPPE yarn for automotive applications, marine applications, aerospace applications, medical applications, defense applications, sports/recreational applications, architectural applications, clothing applications, bottling applications, machinery applications.
The present invention relates to an installation for manufacturing fibre stringers for aerospace structures formed by at least one swivel-mounted cylindrical carousel, peripherally incorporating a distribution of male configured tools and in relation to said carousel a bed capable of lateral movement, incorporating a distribution of female configured tools, a fibre strip applicator head for making fibre laminates on the male configured tools also being arranged in relation to the carousel, which allows making omega-shaped or T-shaped stringers by means of the interaction of each male configured tool of the carousel with a respective female configured tool of the bed.
Disclosed is a Powered Wing Aircraft. A generalized stabilizer/directional vent is used for providing a standard range of aeronautical control. It controls cross winds, directional velocity, directional control, and torque balancing in one simple easy to control device. It is attached to the axles. These improvements can apply to both military and civilian applications.
A bearing assembly and a method of forming a bearing assembly is provided including a housing having a bore. The bore has a generally concave inner surface. The bearing assembly also includes a bearing having an inner member. The inner member is movable about a central axis and is dimensioned to fit within the bore. The inner member has a generally convex outer surface complementary to the concave inner surface of the bore. The housing functions as an outer member of the bearing.
The invention provides an integrated Phased Array (PhA) structural radar transducer, permanently bonded to a structure, that can provide reliable electromechanical connection with corresponding miniaturized electronic SHM device installed above it. The integrated PhA transducer consists of a set of aligned piezo-electric discs with wrap around electrodes for transceiving of elastic ultrasonic waves, plurality of electrical traces and contact pads, several layers of a flexible printed circuit board, electromagnetic shielding between channels and overall, one electromechanical multi-pinned connector and all that integrated into one small unit easy for surface installation by bonding and final application on real structures. The integrated PhA transducer, as a key component of SHM (Phased Array Monitoring for Enhanced Life Assessment) system, has two principal tasks to reliably transceive elastic waves and serve as a reliable sole carrier or support for associated sophisticated SHM electronic device attached above.
An Intelligent Modular Aerospace System (IMAS) is a paradigm shift in the architecture, utility, efficiency, operation, test/checkout, qualification testing and adaptability of an aerospace application system that provides Time/Space/Position Information, Data Acquisition/Processing/Relay, Power Generation/Distribution, avionic solutions, navigation, and command/data handling. IMAS (10) as shown in FIG. 1 is comprised of open architecture stackable modules (12) which are interchangeable and connectable in any order, internally interconnected in a plug and play fashion with an internal raceway (14) containing an input access (16) and output access (18). The resultant IMAS is capable of ingesting any type of external power or data source such as GPS, IMU, communications, command functions and databases such as targeting information. IMAS output includes capabilities such navigation/control logic, avionics steering commands, autonomous flight and flight termination system commands, satellite inter-communications and power from within the modules.
A low profile pass-through electrical connector is designed for aerospace applications. The connector allows voltage and current to pass-thru a conductive wing surface, while maintaining a low profile height for aerodynamic performance considerations. Examples of applications of the electrical connector include power for thin film heaters and communication antennae applications.
A method of treating bearing rolling elements or bearing rings after a hardening and temper heat treatment is disclosed. The method may include treating the bearing rolling elements in a tumbling treatment and then in a duplex hardening treatment. The method may include treating the bearing rings in a peening treatment and then in a duplex hardening treatment. The duplex hardening treatment may also include at least one sequential process segment consisting of subjecting the bearing rolling element & rings to a nitriding process to increase the surface hardness and compressive residual stress. The combined two-step process produces a deep surface/sub-surface residual stress greater than the depth of the maximum operating von-Mises shear stress along with an ultra-hard surface with high magnitude of compressive residual stress. In so doing, the bearing ring and rolling elements will have significantly enhanced rolling contact fatigue resistance and resistance to surface imperfections and debris.
Monolithic metal bodies (e.g., hard aluminum alloys) comprising a continuous microcavity contained within the body are disclosed. The ratio of the cross-sectional area of the metal body to the cross-sectional area of the microcavity may be not greater than 10. The produced metal bodies may be used in structural applications (e.g., aerospace vehicles) to monitor or test the integrity of the metal body.
Metal-coated polymer articles containing structural substantially porosity-free, fine-grained and/or amorphous metallic coatings/layers optionally containing solid particulates dispersed therein on polymer substrates, are disclosed. The substantially porosity-free metallic coatings/layers/patches are applied to polymer or polymer composite substrates to provide, enhance or restore vacuum/pressure integrity and fluid sealing functions. Due to the excellent adhesion between the metallic coating and the polymer article satisfactory thermal cycling performance is achieved. The fine-grained and/or amorphous metallic coatings are particularly suited for strong and lightweight articles, precision molds, sporting goods, aerospace and automotive parts and other components exposed to thermal cycling and stress created by erosion and impact damage.
Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.
Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state, optimal commands of means (10, 11) for controlling the slats, the flaps and the landing gear of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given energy state with a given aerodynamic configuration and a given position of the landing gear.
The device (1) includes means (21) for predicting a stabilizing altitude to which the aircraft will reach a setting approach speed, means (22) for comparing predicted stabilizing altitude to a setting stabilizing altitude and means (24) for establishing an optimized vertical trajectory when the difference between predicted stabilizing altitude and setting stabilizing altitude is more than a predetermined altitude threshold.
Method and device for automatically determining an erroneous height value of a radio altimeter mounted on an aircraft. The device (1) includes means (12, 13, 15) for comparing the duration between two height thresholds to a predetermined reference time, by taking account of current height values of the radio altimeter (2), during an approach phase.
A method and device for determining a consolidated position of a travelling object check the coherence of position values corresponding to a current position of the travelling object and determine a consolidated position for the travelling object based on the coherent position values.
The invention applies particularly to the method and device for displaying forecasts on the flight plan of an aircraft. The method includes representing the craft by a first symbol in its current position and by a second symbol in its future position, modifying the position of the second symbol on the navigation plan in order to change it to a future position, displaying on the viewing screen the first symbol and at the same time the second symbol representing the craft on the navigation plan in a future position and displaying on the viewing screen the navigation data at the instant of the future position of the craft.
A forming tool with a predefined mould portion is provided in a method for producing a reinforced fibre composite component for aviation and aerospace. A forming/support element is moulded by means of the mould portion of the forming tool. A semi-finished fibre product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fibre product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fibre composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fibre composite component. A forming device is provided with a predefined mould portion which holds a forming/support element such that it can be removed.
A system and method for accurately measuring fluid level in a vessel is provided. Generally, the system contains an elongated portion being a coaxial tube having a hollow center, an arm being coaxial in shape, and a sensor containing a transmitter capable of creating and transmitting an excitation electromagnetic pulse for traversing the elongated portion and the arm, and a receiver for receiving reflected pulses, wherein a proximate end of the elongated portion joins a distal end of the arm in a manner to create a waveguide for an electromagnetic pulse provided by the sensor.
The present invention relates to a method for detecting landing quality of an aircraft, comprising: determining whether a vertical speed rate is greater than a first preset value or a vertical acceleration is greater than a second value when the aircraft landing; collecting landing data; generating a landing message based on collected landing data in response to that the vertical speed rate is greater than the first preset value or the vertical acceleration is greater than the second value when the aircraft landing; storing or transmitting the landing message; and determining the landing quality of the aircraft based on the landing data in the landing message
A method is provided for dynamically consolidating items of an aeronautical procedure in order to present to the operator the best action to perform according to the context of all the systems, in order to reduce his cognitive workload faced with an action to be carried out. The method consists, for each item of a procedure, in determining the text of the requested action, in choosing the text of the corresponding response that the crew must perform according to the general state and the configuration of the aircraft, in incorporating in the corresponding item the texts of the requested action and of the corresponding response, in displaying this duly enriched item, in detecting whether the requested action has indeed been accomplished and in displaying the result of this detection.
Method for establishing, by means of a computer, a data sequence for generating a trip, the said method comprising the use of a first set of N data, each data item (POI.sub.i; 1.ltoreq.i.ltoreq.N) identifying a point of interest that may form part of trips, with each data item (POI.sub.i) of the said first set of data there being associated a first identifier (L.sub.p; 1.ltoreq.p.ltoreq.P; P.ltoreq.N) identifying a geographical location where the point of interest identified by the data item (POI.sub.i) is situated, these data being structured in a database by means of the first identifier, the said database indicating, between on each occasion a first pair ((L.sub.r,L.sub.j); 1.ltoreq.r.ltoreq.P; 1.ltoreq.j.ltoreq.P) of geographical locations, a distance (.DELTA.d.sub.rj) and a time (.DELTA.t.sub.rj) for going from the geographical location L.sub.r to the geographical location L.sub.j.
The present invention relates to a method for preparing wholly aromatic polyimide resin with improved heat-resistance. In particular, the present invention provides a method for preparing polyimide resin having enhanced heat-resistance and superior mechanical properties, especially elongation rate and tensile strength at high temperature through liquid polymerization of two kinds of aromatic tetracarboxylic dianhydrides and aromatic diamine whose mixed ratio is properly regulated. Since the polyimide prepared according to the method of the present invention exhibits high heat-resistance and improved ensile strength and elongation rate at high temperature while maintaining intrinsic properties of polyimide, it can be used as a core heat-resistant material of semiconductor and aerospace fields where higher heat-resistance and mechanical properties are required.
A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fibre composite material having a first rigidity to the base layer; attaching a second layer of fibre composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer.
A method of sequestering carbon dioxide in a body of water such as an area of ocean by seeding the water surface with a fertilizer including iron. The seeding is conducted from the air using an aircraft equipped with a device to record or otherwise document the details of the iron distribution, where the method of distribution has been approved in advance for acquisition of carbon sequestration credits by an appropriate agency. Evidence of the success of the application is presented to the appropriate regulatory body and the carbon credits acquired.
A method to improve landing capability for an aircraft is provided. The method includes storing calibrated-offline-reference images of at least one runway in the aircraft and capturing real-time images of a destination runway during an approach to the destination runway. The destination runway is one of the at least one runway. The method further includes comparing the real-time images of the destination runway with the calibrated-offline-reference images of the destination runway to select respective closest calibrated-offline-reference images from the calibrated-offline-reference images for the associated real-time images; evaluating translational differences and rotational differences between associated real-time images and selected closest calibrated-offline-reference images; and determining errors in translational coordinates and rotational coordinates provided by a navigation system in the aircraft during the approach based on the evaluated translational differences and rotational differences.
A method of producing a shaped aluminium alloy panel, preferably for aerospace or automotive applications, from 5000-series alloy sheet. The method includes: providing a sheet made of 5000-series alloy having a thickness of about 0.05 to 10 mm and a length in the longest dimension of at least 800 mm; and stretch forming the sheet at a forming temperature between -100.degree. C. and -25.degree. C., to obtain a shaped aluminium alloy panel. A shaped article formed by the above method is also provided.
Systems and methods for improving situational awareness on an in-trail procedures display. The present invention provides a display with visual identification and indication for aircraft that do not meet the ITP criteria. In the in-trail procedures display, feedback is provided when a pilot selects an invalid ITP flight level, unambiguous feedback is provided to the pilot upon selection of a valid flight level, and valid inter-target aircraft located in intervening flight levels after selection of a valid flight level are positively identified and invalid target aircraft for selection are uniquely identified.
A seat actuation control system includes at least one seat having a plurality of seat devices and a plurality of control modules interconnected over a communication bus. Each module is associated with a corresponding seat control device and is configured to control its corresponding seat device. Each module includes a processor and a memory coupled to the processor and storing program instructions therein which include receiving a status packet from each of the other control modules over the communication bus, processing the status packet for updating the overall system status, and actuating the seat device based on the overall system status. The program instructions further include determining status of the corresponding seat device, generating a status packet including the status information, and broadcasting the status packet to the other modules over the communication bus.
This motorcompressor unit comprises at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the assembly consisting of the motor and the or each compressor being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit. At least one of the compression members comprises at least one aerodynamic member (13) for regulating the angle at which the gas handled by the said stage flows and a motor (16) for controlling the regulating member (13) mounted in the common casing.
A composite laminate for use on an external part of an aerospace vehicle has improved ultraviolet resistance and resistance to microcracking from thermal cycling. The laminate comprises a nanoreinforcement film, a support veil, and a composite layer. The laminate also can have a lightning strike protection layer and an external paint and primer. The nanoreinforcement film can comprise carbon nanomaterial and a polymer resin, and the composite layer has one or more layers of a reinforcement and a polymer resin. The carbon nanomaterial can be carbon nanofibers, and the nanoreinforcement film can have an areal weight of less than about 100 g/m2. The carbon nanomaterial can also comprise carbon nanofibers and carbon nanotubes.
Methods and apparatus for optically detecting an angle of attack for an airfoil using light detection and ranging (LIDAR). To determine the angle of attack, one or more light beam pulses may be emitted from the leading edge of the airfoil into an (apparently) flowing fluid at various emission angles. The emitted pulses may be backscattered by particles in the fluid, and the backscattered light may be received by a detector at the airfoil. By range gating the returning pulses of backscattered light, a fluid velocity may be determined for each of the emission angles. The angle of attack is identified as the emission angle corresponding to the maximum velocity. A parameter (e.g., pitch or speed) of the airfoil may be controlled based on the angle of attack. In this manner, the airfoil may be manipulated or the shape of the airfoil may be adjusted for increased performance or efficiency.
Disclosed are perfluoroethers and perfluoroether compositions useful in high temperature aerospace applications. The perfluoroethers can be adapted for use with various curing chemistries.
A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface.
Disclosed are polyurea compositions comprising the reaction products of a polyformal-isocyanate prepolymer and a curing agent comprising an amine. The compositions are useful as sealants in aerospace applications.
Procedure for the manufacture of large parts of composite material, controlling the thickness of the edges thereof. It relates to the manufacture of a part (11) possessing edge zone (11) in an aeronautical structure through a join with joining plate (23) and backing plate (25) by means of the following stages: a) Definition of interface surface (15) of edge zone (13) to be in contact with joining plate (23); b) Manufacture of first panel (31) possessing the configuration planned for part (11); c) Obtainment of a map of differences between the thickness of first panel (31) and that which it should possess to be coincident with said interface surface (15); d) Manufacture of supplementary panel (33) having a thickness to be coincident with that of said map of differences; e) joining of supplementary panel (33) to first panel (31).
The invention relates to a process for producing a ceramic matrix composite (CMC) part by infiltration of a suspension (S) of a ceramic powder into a fibrous reinforcement (14). A suspension (S) of ceramic powder containing particles of chosen particle size, dispersed in at least one solvent, is prepared. The infiltration of the suspension is carried out in a single step in the fibrous reinforcement (14) positioned between a mould (12) and a permeable membrane (16), which makes it possible to apply a vacuum (V) and to subsequently remove the solvent from the suspension through the permeable membrane (16). The invention applies to the production of large-sized parts of complex shape, in particular in the field of aeronautics and aerospace engineering.
This invention provides an aerodynamic structure attached to the rear cargo body, having doors that swing open, or a single, full-width door, which rolls upwardly. The embodiments provide an aerodynamic structure attached to the rear in a manner that would obscure access to the door(s) in a deployed position, in which the structure reduces drag, yet enables access to the door(s) in a folded position. The folded position allows access to the rear for loading and unloading, and in the case of swinging, hinged doors, allows the doors to be folded through a 270-degree arc, with a minimal sideways projection. The various embodiments also enable relatively rapid and easy transition between the folded position and the deployed position using actuators and/or linkages that tie the folding and deployment of panels of the structure together. This allows selective folding and deployment of the structure without undue effort or strength.
The present invention generally relates to an RFID inventory and expiration date tag for an in-cabin airline metal chemical oxygen generator canister or other in-cabin assets (such as canisters) and a method of using the same. The tag is especially suitable for use in connection with metal oxygen or other gaseous metal canisters used in the aerospace industry. The RFID tag allows for the rapid, efficient, accurate, frequent and easy monitoring of the expiration date of the oxygen generator. The tag has a plurality of stacked layers including layers of polypropylene, polyester, UHF Inlay, fire retardant polypropylene and an acrylic adhesive. The tag extends directly outward from the generator at a tangent to approximately a ninety degree angle with respect to the generator.
A method for searching for airline travel based upon seat characteristics specified by a traveler is disclosed. Travel information is received indicating an origin, a destination, one or more travel dates and one or more seat characteristics other than class of service, all as specified by a traveler. Seat characteristics may include aisle, middle or window seat, bulkhead, row or seat number, individual view screen, power port access, etc. Flights meeting the origin, destination, and date(s) are identified, and then seat maps providing seat information and availability for the identified flights are retrieved. The seat information and identified flights are correlated to identify available seats having the specified seat characteristics, and pricing for those seats is then calculated. Information about the available seats having the specified seat characteristics and the pricing of those seats is then provided for display to a user to select a flight and seat for booking.
An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.
The application discloses a message transmission device for transmitting an SMS message of a mobile device from an aircraft to a ground system. The device comprising an onboard antenna which is connected to a base transceiver station for receiving the SMS message from the mobile device, means for forwarding the message to a mobile switching centre onboard the aircraft and means for emulating status messages. Furthermore, the message transmission device comprises means for transferring the status messages to the mobile device, a splitter for splitting the message into data packets and means for transmitting the data packets to the ground system.
A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system.
Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.
A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.
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.
The Surface Hold Advisor Using Critical Sections is a system and method for providing hold advisories to surface controllers to prevent gridlock and resolve crossing and merging conflicts among vehicles traversing a vertex-edge graph representing a surface traffic network on an airport surface. The Advisor performs pair-wise comparisons of current position and projected path of each vehicle with other surface vehicles to detect conflicts, determine critical sections, and provide hold advisories to traffic controllers recommending vehicles stop at entry points to protected zones around identified critical sections. A critical section defines a segment of the vertex-edge graph where vehicles are in crossing or merging or opposite direction gridlock contention. The Advisor detects critical sections without reference to scheduled, projected or required times along assigned vehicle paths, and generates hold advisories to prevent conflicts without requiring network path direction-of-movement rules and without requiring rerouting, rescheduling or other network optimization solutions.
A computer-based network auction system and method where geographically dispersed aircraft operators solicit competitive quotes for fuel and services from geographically dispersed FBOs, and FBOs submit quotes and communicate and market directly to aircraft operators planning trips to the FBOs airport or nearby airports.
System for detecting wake turbulence (SDWT) of a first aircraft, which can be embedded onboard a second aircraft, comprising: first means (DET1) for determining the roll (Roll.sub.2) of the second aircraft; second determination means (DET2) of an envelope (CRollRef) of reference roll curves which is representative of a wake turbulence created by the first aircraft; means (COMP) for comparing, over a sliding window, the roll (Roll.sub.2) of the second aircraft and the envelope (CRollRef) of reference roll curves; and alarm means (AL) for forewarning the pilot of the second aircraft of the detection of wake turbulence of the first aircraft when the said comparison is below a resemblance threshold (SS).
A method and system are presented for use in determination of the orientation of an aerospace platform with respect to a first rotation axis. A direction of a rotation rate vector of said aerospace platform within a lateral plane intersecting with said first rotation axis is measured and the measured data is analyzed to determine an orientation angle of said aerospace platform about said first rotation axis. While the aerospace platform is in a predetermined-dynamic state movement, a certain direction is determined by measuring a direction of the rotation rate of the aerospace platform within said lateral plane by a sensor assembly mounted on said platform and including at least one rotation rate sensor. An orientation of the platform with respect to said first axis is determined by determining a relation between said certain direction and said known direction within said external reference frame.
An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information.
A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method.
Embodiments of the present invention relate generally to air sanitation and disinfection, and particularly to air sanitation and disinfection for aerospace applications.
A method for wireless communication of aircraft. The method includes, inter alia, in any feasible order, (1) in accordance with detecting a touchdown of the aircraft, assigning a first priority for transmitting information and a second priority for receiving media content; (2) in accordance with detecting an arrival of the aircraft at the gate, assigning a third priority for receiving media content; (3) in accordance with detecting a departure of the aircraft, assigning the first priority for transmitting information and the second priority for receiving media content; and (4) in accordance with detecting a departure ready of the aircraft, assigning a fourth priority for receiving essential media content and the second priority for receiving other media content. The first priority is greater than the second priority; and the fourth priority is greater than the second priority.
Methods, systems and device are provided for smoothing a required time of arrival (RTA) speed transition for an aircraft in a multi-segmented speed profile including at least one preceding region with a first predetermined speed pad and at a speed constrained region with a second predetermined speed pad. Exemplary methods include, but are not limited to determining whether a speed constrained region is engaged by a preceding region based at least in part on a speed of anaircraft. If the speed constrained region is engaged, the instructions determine a revised second speed pad for the speed constrained region. If the speed constrained region is not engaged then the instructions assign a default speed pad as the second speed pad for the speed constrained region. The instructions also compile a new speed profile that is defined by one of the revised second speed pad and the default speed pad for the speed constrained region and transmit commands that accelerate the aircraft to a new speed based on the new speed profile.
Addressed are systems and methods for providing to pilots of landing aircraft real-time (or near real-time) information concerning runway conditions and aircraft-stopping performance to be encountered upon landing. The systems and methods contemplate using more objective data than utilized at present and providing the information in automated manner. Information may be obtained by using conventional ground-based runway friction testers or, advantageously, by using air-based equipment such as (but not limited to) unmanned aerospace vehicles (UAVs).
Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with aspacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.
A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present.
A method and apparatus are provided for operating a network data processing system on an aircraft. A number of operations are performed in a virtual machine on the aircraft. The virtual machine runs on a processor unit in the network data processing system on the aircraft to create a simulated computer environment. The virtual machine accesses resources of the processor unit for performing the number of operations using a host operating system on the processor unit. A current state of the aircraft is identified by the network data processing system. Running of the virtual machine is managed based on the current state of the aircraft and a policy for managing the virtual machine for different states of the aircraft.
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