| Document |
Document Title |
|
WO/2006/081334A2 |
A power situation indicator (100) configured to provide power information in a rotorcraft is presented. The power situation indicator (100) includes a detection unit (105a-f) configured to detect a current value of each of a plurality of...
|
|
WO/2006/024746A1 |
The invention relates to an aircraft display system (1A). The inventive system consists of: a display device (2) comprising information sources (3) which contain information relating to the aircraft and the surrounding environment; infor...
|
|
WO/2006/021815A1 |
A navigation display system for a vehicle comprising processing means for storing a route plan, the route plan having a predetermined position and time at each point along its length, means for displaying the route plan, means for determ...
|
|
WO/2005/120954A2 |
Smart instrumentation and monitoring provide primary engine instrumentation for an aircraft (100). The instrumentation generates real time engine power available data for the entire power regime and flight envelope of the aircraft (100) ...
|
|
WO/2005/093374A1 |
The invention relates to optoelectronic taxi-assistance devices for aircraft, comprising a head-up display which can be used to display information in the pilot's field of vision. The invention is suitable for large civil aircraft of the...
|
|
WO/2005/085065A1 |
A surface-mounted fuselage skin applique panel (19) having an aperture to a reference static air input port (18) is rugged, replaceable, and independently calibratable. The static port skin applique generally conforms to the fuselage sur...
|
|
WO/2005/064277A1 |
Methods and apparatus are provided for interactively building flight paths for entry into an aircraft flight management system (FMS). The apparatus comprises a database containing map information, a display for presenting the map informa...
|
|
WO/2005/054874A1 |
The invention relates to pressure sensors which can be used to measure the aerodynamic flight parameters of an aircraft and, more specifically, to those in which the static and total pressure measurement nozzles (15, 16) are located on a...
|
|
WO/2004/113929A1 |
The invention relates to an in-situ control system, a characterisation device and a method for control of a moving angle of attack probe, for example, mounted on the skin of an aircraft. The probe comprises a moving vane (15), rotating a...
|
|
WO/2004/037643A1 |
The invention concerns equipment features of aircraft instrument panels. The invention is characterized in that it provides an instrument panel, besides a main attitude indicator display system (50, 52, 54) and necessary piloting paramet...
|
|
WO/2004/025386A1 |
The invention concerns a steering aid system for altitude and horizontal speed of an aircraft (4) comprising: a measuring device (22) for delivering a measured signal based on the aircraft altitude and horizontal speed, a common predeter...
|
|
WO/2004/012994A2 |
Systems and methods for sensing air outside a moving aircraft are presented. In one embodiment, a system includes a laser for generating laser energy. The system also includes one or more transceivers for projecting the laser energy as l...
|
|
WO/2004/006203A1 |
A flat panel display (10) for presenting graphical renderings (16) of aircraft flight, operation and system status data to an aircraft pilot renders the data at various predetermined brightness levels depending on the category of data as...
|
|
WO/2003/106949A1 |
The invention relates to a sensor which is used to measure physical parameters in relation to a fluid, such as the total air temperature. The inventive sensor comprises: a fluid intake (1) which is mounted on a profiled body (2); a condu...
|
|
WO/2003/104821A1 |
The invention concerns a device for detecting and recording impacts along several axes on an aeronautic propeller blade comprising an accelerometer (1) integrated inside an aeronautic propeller blade root end (10) and an electronic modul...
|
|
WO/2003/092310A1 |
An aircraft avionics software and database upload transmission/reception system (55) using a cellular data transmission/reception system (40, 42, 44). An aircraft data communications system (10) and method including a communications devi...
|
|
WO/2003/087847A1 |
A differential pressure-induced airflow based approach is used to measure AngleOf-Attack (AOA) or Angle-Of-Sideslip (AOS) for an aircraft. Ports on opposing sides of an aircraft fuselage are coupled by an airway incorporating a mass ai...
|
|
WO/2003/080437A2 |
A mounting bar system permitting infinite adjustability in mounting avionics-components trays (694) and Dzus-mounted avionics in at least one aircraft cockpit instrument panel assembly. Each mounting bar (210) is slotted (270) along its ...
|
|
WO/2003/066433A1 |
A standby instrument (10), such as a standby attitude indicator, including a display, an attitude sensor module, and a speech synthesizer (20) connected to the attitude sensor module. The standby instrument is controllable to cause the s...
|
|
WO/2003/064256A1 |
A real time data retrieving method comprises enabling a control system (10) in an off−land transportation to dial a ground call center (14), activating a data link between the control system (10) and a satellite (16) to allow the satel...
|
|
WO/2003/058257A1 |
An air data sensor for an aircraft has a flush mounted plate (10) at the outside surface of the aircraft and a housing (18) for the sensor within the aircraft below the plate (10). A plurality of holes (16) in the plate (10) provide air ...
|
|
WO/2003/054557A2 |
The invention concerns a multipurpose probe for an aircraft. The probe comprises a mobile vane (1) designed to be oriented in the axis (8) of an air stream surrounding the probe. The mobile vane (1) comprises first pressure sensing means...
|
|
WO/2003/052534A1 |
Disclosed is a method for detecting the takeoff time and/or landing time of a flying device on the basis of air pressure measurement. The air pressure at the flying device is continuously measured before, during, and after takeoff or lan...
|
|
WO/2003/050496A2 |
The invention concerns a multipurpose sensor for aircraft. The sensor comprises means for measuring total pressure (Pt) and means for measuring total temperature (Tt) of an air stream surrounding the aircraft. The means for measuring tot...
|
|
WO2002036427A9 |
An apparatus for providing weather information onboard an aircraft includes a processor unit and a graphical user interface. The processor unit processes weather information after it is received onboard the aircraft from a ground-based s...
|
|
WO/2003/024175A1 |
A design and installation method are provided to improve access to equipment mountable on aircraft equipment racks, including installing modified equipment rack framework on the aircraft, preassembling the equipment on a separate equipme...
|
|
WO/2003/023896A1 |
An equipment rack fabricated from C-channel, flat plate and mechanical fasteners for installation and support of new or retrofit antenna equipment on wide body aircraft. The rack provides direct mechanical connection to aircraft structur...
|
|
WO/2003/021291A1 |
A wide field scanning laser obstacle awareness system (LOAS) comprises: a plurality of first optical elements configured to directa portion of a pulsed laser beam generated by a light source to a light detector, and to direct the pulsed ...
|
|
WO/2003/021290A2 |
A combined system of a LOAS and a LIDAR system comprises: a LIDAR arrangement of optical elements for generating a first coherent beam of light at a first predetermined wavelength; a LOAS arrangement of optical elements for generating a ...
|
|
WO/2003/008908A1 |
A ground proximity warning system including a pitch angle alerting device, the pitch angle alerting device including warning logic having an input that is structured to receive a signal that is representative of the indicated pitch angle...
|
|
WO/2002/095337A1 |
The invention relates to a sensor structure associated with a flow body protruding into a flow for measuring flow states, comprising a structural part (1) having at least two measuring openings (5) to which transfer lines (7) are coupled...
|
|
WO/2002/081307A1 |
A multi-redundant inlaid wiring harness provides for alternate electrical or optical pathways in an aircraft wiring system. A plurality of conduits (25) are inlaid between layers (61, 65) of composite fabric during fabrication of a secti...
|
|
WO2002025212A9 |
A display system according to various aspects of the present invention provides systems and methods for an integrated graphical user interface which facilitates the interactive and dynamic display aircraft data. In accordance with variou...
|
|
WO/2002/070993A1 |
The altimeters (28, 30) which contain within it means for storing the Static Source Error Correction (SSEC) includes means for downloading the SSEC and for transferring it to a new altimeter (32) which may then be used in the place of on...
|
|
WO/2002/041008A1 |
The invention concerns a method for determining aerodynamic parameters of an air stream surrounding an aircraft. The method, based on at least two probes located on the skin of the aircraft, each probe comprising means for measuring the ...
|
|
WO/2002/039058A2 |
Methods and apparatus are provided for airspace navigation. Airspace navigation information for an aircraft is displayed in a first mode, such as, in a horizontal mode. One or more navigation events may then be detected, such as, proximi...
|
|
WO/2002/036428A2 |
A method of providing weather information to an aircraft includes collecting weather information at a data center, transmitting the weater information from the data center to an aircraft via a telephony communication link, and graphicall...
|
|
WO/2002/025215A2 |
The completion of an electronic checklist is facilitated by the automated display of certain data while completing the checklist. The disclosed program presents an automated display of synoptic, navigational, or flight management data fo...
|
|
WO/2002/025213A2 |
A system, method and device for selecting and displaying navigational information is presented which includes a display for showing navigational procedures and/or options, means for selecting or deselecting the procedures and/or options,...
|
|
WO/2002/025208A2 |
The pilot or crew of an aircraft is alerted to the danger presented by wires in the vicinity of the aircraft by a flight instrument which includes a plurality of wire detected display elements (40, 41, 42), advantageously arranged as bar...
|
|
WO/2002/024530A2 |
An aircraft display and control system (100) generally includes a processor (106), a cursor control and selection device (104), a multifunction keyboard (116), an aeronautical information database (110), a geographic database (108), and ...
|
|
WO/2002/025214A2 |
Various embodiments of the invention suitably provide dialog boxes (400, 500, 600, 700, 800, 900) in response to pilot commands so that task parameters may be input or modified. Pilot tasks include 'direct-to', 'hold', 'procedure turn', ...
|
|
WO/2002/025211A2 |
An aircraft display and control system (100) generally includes a processor (106), a cursor control and selection device (104), an aeronautical information database (110), a geographic database (108), and a plurality of display devices (...
|
|
WO/2002/025618A2 |
A system and method for graphically controlling a communication device and displaying its characteristics on a display within a vehicle including a microprocessor, a communication and navigation information window within a portion of the...
|
|
WO/2001/074663A1 |
A standoff arm and probe assembly (20) for a helicopter (10) has a standoff mounting arm (22, 70) that extends outwardly from the helicopter body (18, 72) in a selected direction, preferably forwardly. The standoff arm (22, 70) has an ou...
|
|
WO/2001/067115A2 |
A flow aligned device (12, 66, 100, 122, 150, 176, 214, 234) comprises a probe or vane (12, 66, 100, 122, 150, 176, 214, 234) that will sense angle of attack of an aircraft (10, 74, 106, 124, 164, 180, 210, 231). The flow aligned device ...
|
|
WO/2001/051974A2 |
A method of and an apparatus for coupling a first optical transmission means (10, 42), such as an optical fibre, embedded within an aircraft composite (12, 40) to a second optical transmission means (14), such as an optical fibre, extern...
|
|
WO/2001/051976A1 |
A composite (40) for use in the aircraft construction industry comprise an optical transmission means (42), such as an optical fiber, embedded within a carrier. The optical transmission means is provided with a high-quality optical inter...
|
|
WO/2001/050136A1 |
The invention concerns a device for the in situ angular positioning of an angle-of-attack sensor, of the vane type provided with a flag (121) and fixed on an aeroplane (A¿v?). The invention is characterised in that it consists in direct...
|
|
WO2000021829A9 |
A method of assembling and installing a flip-up pitots system (10) in an ejection seat. A flip-up pitot mount (24) may be fastened to any existing recovery parachute container assembly (12). Mounting holes (26, 34) are created for the va...
|
