3428 results about "Cockpit" patented technology

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.

FIG. 1 shows a light airplane with the installed invention comprising: an Electronic Rear-view Mirror Component (100) in the cockpit usable by the pilot or co-pilot from the adjustment of twin mechanical arms, a Video Local Area Network (V-LAN) Component (3000), several Bug-Eye Sensor Components (2000) for the front-video camera (2004), rear video camera (2008), right video camera (2012), and left video camera (2016), and a Crash Prevention Recorder (CPR) Component (4000).

A wireless piconet transceiver is mounted in a vehicle, and a complementary fixed wireless piconet transceiver is mounted in a garage, service station, police squad car, etc., for communication with the vehicle when parked adjacent thereto. The vehicle establishes a temporary piconet network with the user's home piconet. Vehicle operational statistics are tracked and maintained in a centralized vehicle computer database. This database can be manipulated to store the data desired by the vehicle owner. Via a wireless piconet connection, this database can transmitted to another piconet device such as the owner's computer. This computer system can be part of a wireless piconet, such as Bluetooth, This provides the computer with the ability to communicate with external wireless devices such as a cell phone, PDA, computer, or a cordless telephone. This invention allows for the configuration, or selection of desired vehicle data to be tracked. This configuration can take place on the owner's home computer (or laptop) and consequently transmitted to the vehicle computer using a wireless piconet protocol, e.g., the Bluetooth protocol. Additionally, this configuration can be manipulated by a direct interface to the vehicle provided by the manufacturer. Exemplary vehicle statistics which may be tracked include, but are not limited to, miles per gallon, average miles per hour, maximum MPH, miles driven per trip, driving statistics based on time of day and / or on identified driver, rotations of the engine per minute (RPM), temperature of engine, fuel gauge level, oil pressure, tires, brakes, engine coolant, wiper fluid, global positioning satellite (GPS) system, and / or even compressed voice from inside car cockpit during operation of vehicle.

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.

Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters. When either the first or the second cockpit instrument panel fails, the remaining functional, first or second display, is adapted to provide all of the important flight information data, including airspeed, attitude, altitude, and detailed engine parameters.

Architecture for a multimodal, multiplatform switching, unmanned vehicle (UV) swarm system which can execute missions in diverse environments. The architecture includes onboard and ground processors to handle and integrate multiple sensor inputs generating a unique UV pilot experience for a remote drone pilot (RDP) via a virtual augmented reality cockpit (VARC). The RDP is monitored by an operational control system and an experienced control pilot. A ground processor handles real-time localization, forwarding of commands, generation and delivery of augmented content to users, along with safety features and overrides. The UVs onboard processors and autopilot execute the commands and provide a redundant source of safety features and override in the case of loss of signal. The UVs perform customizable missions, with adjustable rules for differing skill levels. RDPs experience real-time virtual piloting of the UV with augmented interactive and actionable visual and audio content delivered to them via VARC systems.

PCT No. PCT / FR97 / 00147 Sec. 371 Date Sep. 26, 1997 Sec. 102(e) Date Sep. 26, 1997 PCT Filed Jan. 24, 1997 PCT Pub. No. WO97 / 27577 PCT Pub. Date Jul. 31, 1997A process for voice recognition in a harsh environment such as the cockpit of a military aircraft. An acquisition device is connected to an acoustico-phonetic decoding device which is then connected to a recognition supervisor. The acquisition device is also connected to a voice recognition device which is also connected to the recognition supervisor. The voice recognition device is also connected to a dictionary and to a syntax describing device. The syntax describing device is connected to a dialogue model as well as the recognition supervisor.

The present invention includes systems and methods which overcome the shortcomings of the prior art by providing improved control of cursor commands directed by a user (such as a pilot). Various embodiments of the invention include such user interface cursor control enhancements as caging, snapping, hysteresis, combinations of 'relative' and 'absolute' cursor data, integration of discrete button movement with continuous cursor movement, and different gain algorithms. The invention may be implemented in a cockpit display, a flight simulator, a graphical flight planning application, or in any other application having a graphical user interface.

A thin flat panel display for aircraft cockpits. These displays use a dual CPU / graphics generator system to produce simulated aircraft instrumentation displays which are color coded to indicate when one of the graphic generators has not correctly received data from the aircraft system bus. The displays use standard graphic generators and CPUs, and do not require additional software. The displays also allow the aircraft systems to be continuously tested while the aircraft is on the ground. Moreover, the inventive systems include input touch devices which access external memories to display necessary flight and landing information which allow the cockpit crew to expand in detail the external information for display on the flat panels.

A flight data recorder designed for small aircraft captures various onboard flight data in real-time and stores it in non-volatile memory. Recorded data includes aircraft's instantaneous position, altitude, attitude, engine RPM, G forces, flap position, cockpit voice and others. These data are obtained from various sensors which are integrated into the recorder. At the end of a flight the recorded data is downloaded into a computer using a wireless communications data transceiver also integrated into the recorder. It is an inexpensive system that does not require interfacing to any of the aircraft's instruments. It does not require removal or attaching any equipment to be able to download data. In addition to accident investigation, applications include training, preventive maintenance and asset monitoring.

Measurement information of a patient 11 in a clinic, video of a medical procedure site, voice in the clinic, and video information of a body including an affected part of the patient are integrated and sent to a medical cockpit through a network 40. In the medical cockpit, the video of the clinic is outputted on a large screen monitor 73, and the sent measurement information and a plurality of sets of body video information are switched and inset in predetermined positions in the monitor 73 and reproduced. An enlarged moving image of the affected part is reproduced on a main monitor 71. Measurement information of the patient 11, moving image information such as video information of the body including the affected part of the patient or enlarged image information is reproduced on an auxiliary monitor 72. The voice information of the clinic is reproduced by a surround speaker 76. A doctor operates a medical procedure section 62 and controls a knife operating section 121 of a robot 12 in the clinic while seeing the images on the main monitor and the auxiliary monitor.

A head up display system for a vehicle that includes a compact image source for projecting an image. The compact image source may be foldable up toward or into a cockpit ceiling of the vehicle, be positioned within a dashboard of the vehicle, or located at another suitable position. A combiner reflects the projected image with optical power toward an observer for observation. The combiner is positioned so that the observer, in a line of sight, may see a visual exterior view of an outside scene through the combiner and the projected image in the combiner. In a preferred embodiment, the image source includes an illumination system that includes a high power light emitting diode (LED) array assembly. A Fresnel lens array is operatively associated with the LED array assembly for receiving light produced by the LED and providing a nearly collimated light output. A spatial light modulator receives the nearly collimated light output. The preferred combiner is a meniscus combiner that includes a meniscus lens; a multi-layer dichroic coating formed on a first surface of the meniscus lens; and, an anti-reflection coating formed on a second, opposite surface of the meniscus lens. The meniscus combiner preferably utilizes a non-symmetric aspheric meniscus lens.

An aircraft weather radar system is disclosed. The system comprises a radar antenna, aircraft sensors, and a database. The system also comprises a processing device receiving information from the radar antenna and from the aircraft sensors and able to retrieve information from the database. Further, the system comprises a cockpit display coupled to the processing device. The processing device is programmed to estimate storm system characteristics based on the received information from the aircraft sensors and the database and to display the storm system characteristics on a vertical weather profile display using a graphical representation.

A vehicle monitoring system includes a vehicle, a mobile camera device, a transmitter or transmitting transceiver, a receiver or receiving transceiver, and an integrated vehicle cockpit display. The mobile camera device, comprising a processor and a camera, is located within the vehicle or attached to the vehicle for taking an image or video within or outside the vehicle. The transmitter or transmitting transceiver is in communication with the mobile camera device for transmitting the image or the video taken by the mobile camera device. The receiver or receiving transceiver is for receiving the image or the video, taken by the mobile camera device, from the transmitter or the transmitting transceiver. The integrated vehicle cockpit display, built into the vehicle, is in communication with the receiver or the receiving transceiver for displaying the received image or the received video taken by the mobile camera device.

A digital airborne situational awareness system and method. The system is installed on multiple aircraft to generate an airborne network providing collision avoidance without ground control. A global positioning system (GPS) receiver unit is coupled to a microprocessor in each aircraft equipped with the system. A software engine receives the raw GPS data and determines location, speed, flight path direction, and altitude. The software engine conditions the GPS data for display on a cockpit display panel. The conditioned data orients the display with the heading, speed, and altitude data of the host system aircraft. A transceiver section provides data transmission to other airborne receiving units within the approximately forty mile range of the airborne network. The transceiver transmits data packets including reconditioned location (track), altitude, and an aircraft class identifier to other aircraft in the network. The transceiver receives data from other airborne vehicles equipped with the system within the network range. Once the computations of positional data for other aircraft are performed, the positional data is sent to the display processing section for appropriate cockpit display. The software engine develops a set of projections that are compared to the relative speed, flight path direction and altitude of the all other units in the airborne network. These projections determine the threat levels of converging flight paths with limits that provide warning data to the pilot of any pending flight path conflict situation.

Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.

A system and method for automating Air Traffic Control operations at or near an airport. as a complete standalone automated system replacing the need for a human controller to make aircraft movement decisions nor the need communicate with pilots, or as semi-automated, where a controller controls how the system operates. The system with related methods and computer hardware and computer software package, automatically manages manned aircraft, remote controlled UAV and airborne-able vehicles traffic at or near an airport, eliminates ATC-induced and reduce pilot-induced runway incursions and excursions, processes control messages related to aircraft or Pilots, communicates with Pilot over ATC radio frequency, receives aircraft positions, communicates control messages with the aircraft avionics, provides pilots a dynamic map with continuous display of nearby traffic operations, shows clearance and information related to runway operations, warns pilot of runway conditions and turbulence from other operations, warns when landing gear is not locked, displays the pilot emergency exits during takeoff roll, shows the pilot when and where to exit from the runway, shows the pilot where and when to cross a junction, calculates and displays pilot optimal speed and timing on taxiways and junctions for saving fuel, calculates congestions, calculates best taxiway routes, calculates when aircraft can cross a runway, provides directives and information to pilot over CPDLC display or dynamic map for airside operations, alerts and triggers breaks of the aircraft on wrong path or when hold-short bar is breached, displays emergency personnel with routing map and final aircraft resting position for emergency operations, takes over an aircraft operation when aircraft is hijacked or deviates from the flight plan, provide standalone or manned Remote Tower functionality, Records and retains all information related to airport airside operations including aircraft positions and conditions from sensors and reports for runways, junctions and taxiways, Records and retains aircraft data and cockpit voice to ground-based servers to eliminate black-box requirements, calculate future weather and airport capacity from aircraft at or nearby airport, coordinates handoff operations with other ATC positions, interfaces with ACDM systems, airport operations center, flow center and network operations center.

A dynamic wake avoidance system utilizes aircraft and atmospheric parameters readily available in flight to model and predict airborne wake vortices in real time. A novel combination of algorithms allows for a relatively simple yet robust wake model to be constructed based on information extracted from a broadcast. The system predicts the location and movement of the wake based on the nominal wake model and correspondingly performs an uncertainty analysis on the wake model to determine a wake hazard zone (no fly zone), which comprises a plurality of “wake planes,” each moving independently from another. The system selectively adjusts dimensions of each wake plane to minimize spatial and temporal uncertainty, thereby ensuring that the actual wake is within the wake hazard zone. The predicted wake hazard zone is communicated in real time directly to a user via a realistic visual representation. In an example, the wake hazard zone is visualized on a 3-D flight deck display to enable a pilot to visualize or “see” a neighboring aircraft as well as its wake. The system substantially enhances the pilot's situational awareness and allows for a further safe decrease in spacing, which could alleviate airport and airspace congestion.

A flight deck display system for an aircraft or other vehicle includes a first data source of visual feature data that is indicative of visual features of a location of interest, a second data source of flight data for the aircraft, a processor architecture, and a display element. The processor architecture is operatively coupled to the first data source and to the second data source, and it is configured to process the visual feature data, process the flight data, and, based upon the visual feature data and the flight data, generate image rendering display commands. The display element receives the image rendering display commands and, in response thereto, renders a dynamic graphical representation of the location of interest using the visual feature data. The dynamic graphical representation of the location conveys an amount of visible detail that varies as a function of the flight data.

A head up display includes an image source, collimating optics, and a combiner. The collimating optics are disposed between the combiner and the image source. The combiner receives collimated light from the collimating optics at an input and provides the collimated light to an output. The collimating light travels from the input to the output within the combiner by total internal refraction. An input diffraction grating is disposed in a first area and an output diffraction grating is disposed in a second area. The first area is smaller than the second area.

An Aerodrome providing safe storage for Unmanned Aerial Vehicles (UAVs) that includes an enclosure to protect UAVs from the elements (weather). The Aerodrome includes an enclosure, a foldable flight deck, a service interface, and a telescoping video and audio feed unit. The aerodrome can be remotely operated, and can be mounted on a roof of a structure or vehicle, allowing a completely automated service of the UAV without the need of a person being physically present in the vicinity of the UAV.

A device for programming industry standard autopilots by unskilled pilots. The effect of the invention is such that when the invention is employed in a flying body comprising an industry standard autopilot with a digital flight control system, the invention provides for the safe operation of any aircraft by an unskilled pilot. The device additionally affords skilled pilots a more rapid and simplified means of programming autopilots while in flight thus reducing a skilled pilot's cockpit workload for all aircraft flight and directional steering, way points, and aircraft flight functions reducing the possibility of pilot error so as to effect safer flight operations of an aircraft by affording a skilled pilot to direct aircraft steering and function while under continuous autopilot control.

A flight information display for the flight deck of an aircraft showing a pictorial side view of the flight path or the area directly in front of the aircraft area having a selected distance of at least 0.5 nautical miles, comprising (a) a pictorial representation to scale of the profile of the highest elevations of a swath of terrain along said path or area, (b) an icon positioned on the left or right side of the display representing the aircraft, the altitude of which is to scale with the height of the terrain, and (c) an altitude reference scale; wherein the width of the swath is at least 0.1 nautical miles and no greater than the distance of the minimum accuracy of the means for determining the aircraft's location.

A flight control system for aircraft, such as for a vehicle with a ducted fan propulsion system which also produces rotary moments and side forces for control purposes. The flight control system of the present invention is designed in a manner that will ensure the safety of the vehicle in event of a malfunction in any one of its channels and enable the flight to continue down to a safe landing.

A system to monitor aircraft equipment, having a chassis, defining an interior compartment, an arrangement configured to accept input data of at least one aircraft parameter, the arrangement configured to be placed within an aircraft, crash survivable cockpit voice and flight data recorder, and a power supply arrangement connected to arrangement configured to accept input data and the recorder.