47963 results about "Airplane" patented technology

Vehicle lighting methods and apparatus, in which an LED-based light source is configured to generate at least visible radiation associated with a vehicle. The light source is controlled such that the generated visible radiation has a variable color over a range of colors including at least three different perceivable colors. Examples of vehicles in which such methods and apparatus may be used include, but are not limited to, an automobile, airplane, boat, non-motorized vehicle, etc. The LED-based light source may be disposed inside the vehicle (e.g., dashboard, instrument panel) or outside the vehicle (e.g., brake lights, undercarriage lighting), and may be controlled to generate white light as one of the perceivable colors. A user interface may be employed to facilitate an adjustment of the variable color of the generated visible radiation. Additionally, information relating to at least one condition associated with the vehicle may be employed to control the LED-based light source such that the variable color of the generated visible radiation is based at least in part on the condition associated with the vehicle.

Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start. Detailed methods are disclosed to use the new components for routine ground-testing and maintenance and for the enhancement of flight safety, minimization of engine component damage, and extension of engine-out flying range in the case of an emergency in-flight engine shutdown.

Detecting video phenomena, such as fire in an aircraft cargo bay, includes receiving a plurality of video images from a plurality of sources, compensating the images to provide enhanced images, extracting features from the enhanced images, and combining the features from the plurality of sources to detect the video phenomena. Extracting features may include determining an energy indicator for each of a subset of the plurality of frames. Detecting video phenomena may also include comparing energy indicators for each of the subset of the plurality of frames to a reference frame. The reference frame corresponds to a video frame taken when no fire is present, video frame immediately preceding each of the subset of the plurality of frames, or a video frame immediately preceding a frame that is immediately preceding each of the subset of the plurality of frames. Image-based and non-image based techniques are described herein in connection with fire detection and/or verification and other applications.

An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline axis. A plurality of circumferentially spaced apart struts extend between the first and second structural rings. Forward and aft sump members having forward and aft central bores are fixedly joined to forward and aft portions of the turbine frame respectively. A frame connecting means for connecting the engine to an aircraft is disposed on the first structural ring. The frame connecting means may include a U-shaped clevis. The frame may be an inter-turbine frame axially located between first and second turbines of first and second rotors of a gas turbine engine assembly. An axial center of gravity of the second turbine passes though or very near a second turbine frame bearing supported by the aft sump member.

A vertical take-off and landing vehicle comprised of a fuselage having a front, a rear, and two lateral sides and a set of four thrusters set to the front, the left, the right, and the rear of said fuselage. The thrusters are either independently powered thrusters or could utilize a single power source. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with up to two thrusters inoperative. The thrusters are comprised of a set of two counter rotating propellers both of which creates lift. The two counter rotating propellers cancel out the torque effect normally created by using only one propeller. The Ducted fan units being movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust using a set of servos and gears.

The MULTIBODY AIRCRANE performs relative positioning, predictive control, and ballast control to achieve very heavy-lifting tasks on land or sea. Such tasks allow station keeping and precise transfer of very heavy payloads between ships underway. This scalable multibody system features three subcomponents: AIRSHIP, SKYCRANE and LOADFRAME. This semi-autonomous system combines aerodynamic (kinetic) and aerostatic (buoyancy force) lift with efficient power and propulsion. During low-speed flight, the Airship and Skycrane are decoupled but linked via a reelable Tether Control Line. Beneath the Skycrane, centered on its hull, a patented NIST (National Institute of Standards and Technology) RoboCrane (featuring a computer controlled six degrees of freedom (DoF) cabling system,) is attached, to precisely suspend and control a Loadframe, with or without payload. During subsonic forward flight, these Airship and Skycrane are coupled as a single airframe (fuselage and delta wing.)

A data collection and distribution system for monitoring aircraft in flight, on the ground and at the gate or terminal for monitoring critical and catastrophic events, managing the emergency during such an event, and for investigating the event. The system generates, transmits and collects critical data generated by monitoring equipment onboard an aircraft or other commercial transport and selectively displays the data on a cockpit display console as well as for downloading, transmitting and displaying data at external monitoring and response stations, including fixed ground stations, roving ground stations and chase aircraft or vehicles. Digital surveillance information is collected, processed, dispatched, and log via remote control and access. The system includes a variety of system appliances such as surveillance cameras, sensors, detectors, and panic buttons and accommodates legacy equipment. Within the commercial transport, the system maybe hardwired or may use wireless transmission and receiving systems.

A method and system for efficient distribution of power using wireless means, and a system and method for wireless power distribution to provide electric devices, such as vehicles with a way to continuously and wirelessly collect, use and charge their power systems and thereby use the transmitted power for operation. The system and method allows a hybrid, simplified and less costly way to charge devices, such as vehicles so that the devices continuously operate while charging/recharging.

The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

The Unmanned Aircraft Systems ground support platform is a portable, multifunctional apparatus to accommodate UAS (Drone, UAV) landings, takeoffs, idle time, maintenance, retail merchandise product display and package delivery support within the UAS recreational and business industry. The Unmanned Aircraft Systems ground support platform will provide stability and cleanliness of a Unmanned Aerial Vehicle. Ownership identification is intergraded into the base platform.

The invention relates to a ground-based wireless cellular communication system (1a) for providing in-flight broadband mobile communication services, comprising: at least one ground-based base station (2) adapted for generating at least one cell (C1, C2) defining a solid angle of the space surrounding the base station (2), the ground- based base station (2) further comprising at least one antenna array (5a, 5a) using two-dimensional-beamforming for generating at least one beam (6a-c, 7a-c) for serving at least one airplane (8a-c, 8c-e) in the space covered by the at least one cell (C1, C2) using spatial-division multiple access, SDMA. The invention also relates to an airplane equipment for providing in-flight broadband mobile communication services, comprising: at least one antenna for exchange of user data with the ground-based wireless cellular communication system (1a), a transceiver unit connected to the at least one antenna for handling the air-to-ground and ground-to-air communication with the ground-based wireless cellular communication system (1a), and an inside-airplane communication system for distributing the user data to and from terminals within the airplane.

The present invention is a system and method for providing flight management to one or more aircraft via a communication link between a fight management system located outside the aircraft and a flight management system located inside the aircraft. Remote flight management system may monitor and control navigation functions, substantially reducing pilot or crewmember workload. Optimized simultaneous flight management of multiple aircraft located within a specified area or within a specified fleet may be provided. Remote flight management system may be suitable for monitoring and controlling navigation functions for multiple aircraft from a single location.

An airborne cell phone in-flight entertainment (IFE) system uses a cell phone for calls and IFE requests by dialing appropriate numbers. A pico cell receives the calls and the IFE requests. A soft switch switches the calls and IFE requests according to the telephone number. A transceiver receives the calls from the soft switch and sends them to a ground station that directs them to a telephone system. A media server receives IFE requests and provides IFE to the cell phone. A direct broadcast satellite (DBS) receiver on the aircraft receives DBS signals. A transcoder converts the received DBS signals from one compressed video format to another. A broad-to-connection protocol conversion process receives converted format DBS signals and converts them to video content blocks, stores the video content blocks to a continuously updated buffer and presents them to the media server and then to the cell phone.

A vehicle based data collection and processing system which may be used to collect various types of data from an aircraft in flight or from other moving vehicles, such as an automobile, a satellite, a train, etc. In various embodiments the system may include: computer console units for controlling vehicle and system operations, global positioning systems communicatively connected to the one or more computer consoles, camera array assemblies for producing an image of a target viewed through an aperture communicatively connected to the one or more computer consoles, attitude measurement units communicatively connected to the one or more computer consoles and the one or more camera array assemblies, and a mosaicing module housed within the one or more computer consoles for gathering raw data from the global positioning system, the attitude measurement unit, and the retinal camera array assembly, and processing the raw data into orthorectified images.

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

Spatially Integrated Small-Format Aerial Photography (SFAP) is one aspect of the present invention. It is a low-cost solution for bridge surface imaging and is proposed as a remote bridge inspection technique to supplement current bridge visual inspection. Providing top-down views, the airplanes flying at about 1000 feet can allow visualization of sub-inch (large) cracks and joint openings on bridge decks or highway pavements. On board Global Positioning System (GPS) is used to help geo-reference images collected and facilitate damage detection. Image analysis is performed to identify structural defects such as cracking. A deck condition rating technique based on large crack detection is used to quantify the condition of the existing bridge decks.

A method and system for airport or other building security where passengers or persons entering a building approach a check-in point or check-in counter and must undergo a positive identification (ID) by fingerprint scan, retinal scan, or an other means of positive identification. A digital photograph can then be taken of the person. This data plus the positive ID data and optional data about the person including a scan of a government supplied ID like a drivers license or passport is entered in a database and checked against various law enforcement databases such as FBI or others for law enforcement interest in the person. The person is given an electronic smartcard that has wireless capability. The person carries the smartcard while in the airport or building. The system is notified when the person enters a secure gate area, boards or leaves an aircraft, etc. In addition, the system can determine if a person is carrying more than one smartcard or if a card has been abandoned. The system detects and tracks any undesirable person in the airport or building an provides a means for apprehending the person by security or law enforcement personnel. In addition, immigration or customs can be notified about any undesirable person arriving in an airport. The system allows airline personnel and security personnel to know when an unexpected or unwanted event or person is in the system.

A light fixture for housing LED units is provided. The light fixture has a housing that has a substantially H-shaped cross section. The housing has a crossbar with a series of mesas defined on its upper surface. A group of LED units is attached to each of the series of mesas, each LED unit being attached with a thin layer of adhesive. The LED units are electrically insulated from the housing by either the adhesive, which may be electrically insulating, or by an electrically insulating coating on the housing.