8481 results about "Aviation" patented technology

The invention relates to improved methods and forms for automatically and non-unobtrusively to detect, without human interpretation, the identification of people(s), object(s), and other, with various methods utilized in connection to creating, storing, adding, connecting, modifying, sharing, inputting, recalling, authorizing, approving, tracking, generating, formatting, monitoring, accessing, locating, deleting, controlling, linking, collecting all types of data and information, and generating at least one type of identifiable communications information related to anyone or anything, and in and/or around any type of environment, such as an airport(s), airline(s), and/or other aviation location(s), theme park, amusement park, aquarium, cruise ships, tourist location, hospitals, buildings, government complex, malls, customs boards, sports events, parking, manufacturing, hotels, resorts, clubs, retail, elevators, utilities, museums, libraries, as well as other types of location(s), among other environments.

A noise-free portable EEG system is provided. The system has hardware and software and can evaluate mental state quantitatively. The quantitative data of mental states and their levels can be applied to various areas of brain-machine interface including consumer products, video game, toys, military and aerospace as well as biofeedback or neurofeedback.

A personal portable integrator is used to integrate the services of an arbitrary audio delivery device such as an MP3, CD, DVD, radio, or other media player, with the services of an arbitrary two-way communication device such as a mobile phone, or a two-way radio such as a walkie talkie, citizen band radio (e.g. CB), HAM radio, marine or aviation radio, and the like. The portable integrator receives and provides input and output signals from both the audio delivery device and the two-way communication device, thereby enabling a user to listen to music or other audio material and receive and place phone calls on a mobile phone simultaneously. The portable integrator provides these services by switching between the audio and communication devices, mixing signals received therefrom, and optionally enabling a user to reduce the volume or mute the signals as desired.

An airborne weather radar system that detects potentially hazardous weather conditions associated with storms and includes a radar display featuring visual indications of these conditions. The radar display includes a vertical situation display having iconal representations and symbolic icons indicative hazardous weather conditions and aviation hazards along the aircraft's flight path not otherwise immediately apparent or shown on standard weather radar displays. The system includes processes for detecting and predicting hazardous weather conditions such as overshooting thunderstorm tops and vaulted thunderstorm energy and serious hazards such as turbulence and hail.

A system and method for construction estimation using aerial images is provided. The system receives at least one aerial image of a building. An estimation engine processes the aerial image at a plurality of angles to automatically identify a plurality (e.g., perimeter and interior) lines in the image corresponding to a plurality of features of a roof the building. The estimation engine allows users to generate two-dimensional and three-dimensional models of the roof by automatically delineating various roof features, and generates a report including information about the roof of the building.

The present invention relates to the management, on board an aircraft, of the aeronautical digital telecommunications networks ACARS and ATN. It covers a method for automatic choice of the transmission sub-network of the ACARS or ATN networks which is most appropriate for the exchange of digital messages with the ground, taking account of the capabilities of the equipment of the aircraft, of that existing on the ground in the area overflown, of the costs and of the reliabilities of the possible links, and of the preferences of the pilot, of his airline and of the control services. This method consists principally in the creation and updating of a database containing information: costs, performance levels, security/reliability, aircraft configuration, availabilities of the communications sub-networks as well as the stipulations by the pilot, by his airline and by the control services, and in the automatic selection of a communications mode via a sub-network of the ACARS or ATN networks, taking into account an order of preference established on the basis of criteria based on the information contained in the database (342).

A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems.. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial counter rotating rotor drive providing lifting power with an inherent aeronautical stability; Auxiliary propellers that face the direction of flight and are located on opposite sides of said coaxial Rotary-wing apparatus and enable flying forwards, backwards and perform yawing; A rotary-wing coaxial helicopter toy that is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids

In an anti-hijacking system for autopilot equipped aircraft, a transceiver communicates with at least one remote guidance facility. A panic button is activated by flight crew in case of hijacking. A manager is coupled to the transceiver and the panic button, as well as existing avionics including the aircraft's master computer and autopilot. Optionally, a relay is coupled between the pilot controls and selected aircraft flight systems. The manager recognizes predetermined override inputs, such as activation of the panic button or receipt of override signals from the remote guidance facility. Responsive to the override input, the manager deactivates on-board control of selected aircraft flight systems and the autopilot system, and directs the autopilot to fly the aircraft to a safe landing. Flight routing and landing instructions are obtained from the remote guidance facility, or by self-evaluating nearby airports in view of the aircraft's position and various preestablished criteria.

Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.

A fiber-reinforced thermoplastic composite material having an advantageous combination of smoke generation, heat release, and mechanical property characteristics. The composite generally comprises a fiber-reinforced thermoplastic core containing discontinuous reinforcing fibers bonded together with one or more thermoplastic resins. The core material may further comprise at least one first skin material applied to a first surface of the core and/or one or more second skin material applied to a second surface of the core material. The thermoplastic core material has a maximum smoke density D_s (4 minutes) of less than 200 as measured in accordance with ASTM E662, a maximum heat release (5 minutes) of less than 65 kW/m² as measured in accordance with FAA Heat release test FAR 25.853 (a) Appendix F, Part IV (OSU 65/65), and an average total heat release (2 minutes) of less than 65 kW/m² as measured in accordance with FAA Heat release test FAR 25.853 (a) Appendix F, Part IV (OSU 65/65). The invention is useful in the manufacture of articles for aircraft, automotive, railcar, locomotive, bus, marine, aerospace and construction in which the certain advantages may be provided over other materials utilized for such applications.

The invention provides a ceramic material for 3D (three-dimensional) light curing forming printing. The ceramic material is prepared from the following ingredients in percentage by weight: 25 to 85 weight percent of light curing resin and 15 to 75 weight percent of modified inorganic powder. The invention also further provides a preparation method and a use method of the ceramic material for 3D light curing forming printing. The ceramic material for 3D light curing forming printing provided by the invention is applicable to the preparation of a ceramic product by 3D light curing forming technologies such as the light curing laser fast forming and digital-based light processing projection curing forming. The defect of the current condition that the light curing forming technology in the prior art is not used for producing the ceramic product is overcome; the dimension precision of the obtained ceramic product is high; the 3D printing forming of various ceramic elements in complicated shapes can be realized; the ceramic material can be applied to aviation and aerospace industry, the medical field and the industrial field.

A present novel and non-trivial system, module, and method for constructing a flight path used by an avionics system are disclosed. A processor receives flight plan data and object data associated with terrain and obstacles. Free cells are extracted above the objects using a recursive space decomposition technique, and a reference path is formed through traversable free space determined from the availability of free cells. In an additional embodiment, threat data associated with hostile military weaponry and significant meteorological conditions could affect the availability of free cells. A genetic algorithm applying genetic operators which include mutators is employed with aircraft kinematic constraints to refine the reference path used to form a population of best path candidates. When a best path is reached after cycling through a re-generation process of path candidates, flight path data representative of the best path is generated and provided to at least one avionics system.

Various embodiments of the invention relate generally to systems for providing active vertical control of an airship. More particularly, at least one embodiment of the invention relates to a system for actively controlling the aerostatic lift of an airship by manipulating the ratio of air to lifting gas contained within the airship, and thus the overall mass of the airship. This manipulation is accomplished by actively compressing and/or decompressing the lifting gas or internal air, with the resulting pressure differential borne primarily by the hull and/or an internal pressure tank depending upon the configuration.

The invention relates to a preparation method of high-performance water-based anticorrosion paint. The high-performance water-based anticorrosion paint comprises 30-60 parts of inorganic material resin, 0.5-30 parts of polyaniline-based nano composite material, 0-30 parts of curing agent, 0.1-1 part of defoaming agent, 0.1-1 part of dispersant and 0.1-1 part of leveling agent. Since the high-performance water-based anticorrosion paint does not contain organic resin or organic solvent, the paint has the advantages of heat resistance, wear resistance, weather resistance, oil resistance, fire resistance and environmental protection; the paint also has the advantages of simple preparation technique, strong binding force with metal, and low cost, can be cured at normal temperature, and can be widely used for corrosion protection in the fields of aviation, navigation, chemical engineering, electronics and the like.

The invention discloses an avionics system suitable for a multi-purpose unmanned aircraft. A 1553B dual-redundancy bus framework is adopted in the avionics system. The avionics system consists of a main processor unit, a universal interface unit, a 1553B bus, a mass memory, an airborne monitoring terminal, a task load, an execution mechanism and a sensor assembly. The devices have the connection relationships that: the main processor unit, the universal interface unit, the mass memory, the airborne monitoring terminal and the task load are connected with the 1553B bus through a 1553B special electric connector, and the 1553B special electric connector serving as a bus module connects all the devices attached to the bus together; a steering engine controller is connected with the universalinterface unit through an RS422 interface; and the sensor assembly is connected to the universal interface unit through interfaces of serial RS422/RS232/RS485, an ARINC429 bus, a CAN, analogue AD/DA and discrete DIO and the like. The avionics system has the characteristics of strong multi-task expandability, multi-redundancy high reliability, rich data interfaces and strong calculation and processing capabilities, and can well meet the application requirement of 'one platform and multiple purposes' of the unmanned aircraft.

A method and system for multi-spectral imagery acquisition and analysis, the method including capturing preliminary multi-spectral aerial images according to pre-defined survey parameters at a pre-selected resolution, automatically performing preliminary analysis on site or location in the field using large scale blob partitioning of the captured images in real or near real time, detecting irregularities within the pre-defined survey parameters and providing an output corresponding thereto, and determining, from the preliminary analysis output, whether to perform a second stage of image acquisition and analysis at a higher resolution than the pre-selected resolution. The invention also includes a method for analysis and object identification including analyzing high resolution multi-spectral images according to pre-defined object parameters, when parameters within the pre-defined object parameters are found, performing blob partitioning on the images containing such parameters to identify blobs, and comparing objects confined to those blobs to pre-defined reference parameters to identify objects having the pre-defined object parameters.

An un-manned airborne vehicle (UAV), for acquiring aeromagnetic data for geophysical surveying at low altitude on land or over water, comprising an extended fuselage that is adapted to hold and maintain magnetometer and a magnetic compensation magnetometer at a minimum distance from the avionics and propulsion systems of the UAV. The magnetometer measures magnetic anomalies and the magnetic compensation magnetometer measures magnetic responses corresponding to the pitch, yaw and roll of the UAV. A data acquisition system stores and removes the magnetic response measurements from the magnetic anomaly measurements. The data acquisition system also stores a survey flight plan and transmits the same to the avionics system. The generator of the UAV is shielded and the propulsion system is stabilized to reduce magnetic and vibrational noises that can interfere with the operation of the magnetometer.

The present invention relates to a novel synthetic route of a liquid chain hydrocarbon fuel totally independent of fossil energy based on a lignocellulose raw material to obtain a platform compound. The method includes three parts: 1) preparing oxygen-containing organic compounds with carbon chain length of 8-16 through the acid-catalyzed alkylation reaction by taking lignocelluloses-based carbonyl-containing platform compounds and furan platform compounds as raw materials on a novel solid catalyst; 2) effectively removing carbon-carbon double bonds and carbon-oxygen double bonds to prepare saturated oxygen-containing organic compounds by hydrogenation of the alkylated product; and 3) conducting hydrodeoxygenation for the hydrogenated alkylation product by using a metal-solid acid bifunctional catalyst to obtain the biomass aviation kerosene or high grade diesel fuel with the carbon chain length of 8-16 and having a high energy density and stability.

The invention discloses a method for testing the assembly performance of a rotor of an aircraft engine, which comprises the following steps of: firstly exciting and vibrating a rotor of an aircraft engine with a vibration exciter; obtaining a multiple carrier-coupled impulse response signal of the rotor of the aircraft engine with a vibrating sensor and signal-acquiring system software; analyzing the obtained multiple carrier-coupled impulse response signal of the rotor of the aircraft engine by means of dual-tree complex wavelet transform to obtain eight signal carrier-coupled impulse response signals of the rotor of the aircraft engine; and distilling the average assembly performance index of the obtained eight signal carrier-coupled impulse response signals of the rotor of the aircraft engine, wherein the assembly performance of the rotor of the aircraft engine is judged to be qualified if the obtained average assembly performance index is larger than or equal to 10, and the assembly performance of the rotor of the aircraft engine is judged not to be qualified if the obtained average assembly performance index is less than 10, so that the rotor needs to be repaired.

The invention provides a high-performance thermal insulation material and a preparation method thereof. The thermal insulation material comprises silicon dioxide aerogel and a fiber material, wherein, the silicon dioxide aerogel takes silicon dioxide hydrosol as a raw material, and is prepared by adding a catalyst. The method comprises the following steps: sol preparing, sol dipping, gelating, gel ageing, hydrophobization treating and drying and the like. The method can conveniently and selectively prepare the materials of planes, abnormal-shape surfaces and multiple sizes, has simple and convenient operation and small environmental pollution. The material has excellent mechanical performance, good high-temperature stability and heat insulation performance, and has wide application prospect in the fields of civilian industries, space flight and aviation industries, military industries and the like.

The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

The invention provides a non-contact free space eye-gaze tracking method suitable for man-machine interaction. The method comprises the steps of positioning and tracking a face and eyes in real time, extracting eye movement biological characteristic information, building an eye movement model based on the eye movement biological characteristic information, building a mapping relational model of the eye movement model and an eye-gazed object and the like. The non-contact free space eye-gaze tracking method suitable for the man-machine interaction relates to multiple crossed fields of image processing, computer vision, pattern recognition and the like and has wide application prospect in the fields of new-generation man-machine interaction, disabled people assisting, aerospace relating field, sports, automobile and airplane driving, virtual reality, games and the like. In addition, the method has great practical significance for improvement of the life and self-care level of disabled people, building of a harmonious society and improvement of independent innovative capability in the national high-and-new technical fields of the man-machine interaction, unmanned driving and the like.

The scene matching method for raising navigation precision includes the following steps: 1. for the topographic scene matching module in combined navigation system to read in topographic data based on the digital topographic picture; 2. to search mapping point in the topographic picture based on the current geographic location the inertial navigation system obtains; 3. to intercept the reference map data from the topographic picture around the mapping point; 4. matching the measured map and the reference map; and 5. correcting inertial navigation with the matched result so as to raise the precision of inertial navigation system greatly. One simulating combined navigation system is also disclosed, which includes an aviation trace planning module, a flight control module, an aviation trace generator, an inertial navigation module, a topographic scene matching module matching module and an image displaying module. It has high locating precision, high autonomy and excellent man-computer operation interface.

A system operates to guide an aircraft to or along a route designed to maintain the aircraft within a safe glide distance of an acceptable emergency landing area. The system uses a database of emergency landing areas with glide characteristics of an aircraft to determine a route that minimizes travel time or other specified parameter, while keeping the aircraft within a safe glide distance of a landing area in the database meeting the landing requirements for the aircraft.

The invention discloses a flight program design system for performance-based navigation (PBN), a verification platform and a verification method, belonging to the field of aerial navigation. The program design system is based on an AIXM (Aeronautical Information Exchange Model) core database; a program protection region can be automatically drawn, an obstacle is evaluated, and a chart is generated; and thus, functions such as seamless connection and the like of the PBN program protection region and the conventional flight program protection region can be realized. According to the system, the chart can be automatically generated according to data finished by the flight program design, customized edition and modification can also be realized according to requirement, and program design and publishing are finished at one time. By using the flight program design system, the verification platform and the verification method, the PBN program can be directly added in a navigation database of the verification platform, and the navigation database can be edited and modified in a verification process. In addition, a visual scene database is increased; the defects and the disadvantages of the program design can be directly discovered according to geomorphology in a visual scene when the PBN flight program is verified; and the program is further modified perfectly.

An intelligent communications capability that enhances legacy military tactical datalink systems by creating an interface between disparate civil and military communications systems onboard military aircraft, ground vehicles, and ground-based communications infrastructures. This capability performs various information management tasks to interface with avionics systems, ground vehicle computer systems, and ground-based infrastructure computer systems. The invention enhances message processing through automation in areas such as data collection, incoming message handling, outgoing message construction, communications network management, and message priority management and routing. The invention also incorporates learning techniques to improve the overall efficiency of integrated military missions, operations, and maintenance in areas such as intelligent consolidation of datalink information, intelligent message distribution, and adaptive message re-routing in response to communications network failures. These enhancements will benefit the military by improving mission effectiveness with real-time information integration and management while reducing their support costs.

A miniature, unmanned aircraft having interchangeable data handling modules, such as sensors for obtaining digital aerial imagery and other data, and radio transmitters and receivers for relaying data. The aircraft has a microprocessor for managing flight, remote control guidance system, and electrical supply system. The data handling modules have an aerodynamic housing and manual fasteners enabling ready installation and removal. One or more data acquiring sensors or data transferring apparatus and support equipment such as batteries and communications and power cables are contained within the module. A plurality of different modules are preferably provided. Each module, when attached in a preferred location below the wing, does not significantly alter the center of gravity of the airframe. Preferably, each module contains the supervisory microprocessor so that the microprocessor need not be part of the airframe.

A GPS device adapted and operable to download and store, receive, or otherwise obtain and display any of a variety of different types of geo-referenced raster images, such as, for example, aerial photographs, and to integrate those images into a scheme of information which is relevant to navigation and travel generally.

A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and comprises an intake (12) and a thrust reverser unit (31). The thrust reverser unit (31) is formed by two generally C-shaped portions (31a, 31b). The thrust reverser unit (31) is openable to provide access to the accessories (34) and the core engine (9). The nacelle (55) further comprises a fan containment casing (33) that is integral with the intake (12).