17769 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 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.

A method and system for a plurality of airplanes in flight to receive from and send to a plurality of ground stations broadcast and communication signals through a single or a plurality of geostationary satellites, wherein at least the mobile link between said airplanes and said satellite, uplink or downlink, uses the high frequency radio waves at 17 GHz or higher, such as Ka-band. The fixed link between said satellite and said ground stations may use any radio frequencies below the frequencies used to communicate between the satellite and the aircraft. The lower frequencies tend to be less susceptible to rain attenuation and hence suitable for closing the fixed broadcast and communication link. Frequencies such as C-band or Ku-band, or even Ka-band, are applied between satellite and ground such that the available link margin is sufficient to overcome rain attenuation at said ground stations. Said satellite carries a plurality of transponders that may include a plurality of frequency converters to enable the conversion between different frequencies. Said satellite generates a plurality of spot beams, shaped or unshaped, which collectively cover the flight routes of said airplanes, preferably the geodesic path between two highly populated regions.

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 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.