Abstract: A method for determining a currently obtainable climb gradient of an aircraft by determining an estimated aircraft weight as a function of phase of flight, determining the current aircraft weight as a function of the current dynamic pressure, the unaccelerated lift of the aircraft, and the wing surface area of the aircraft during steady-state flight, updating said estimated aircraft weight as a function of the current aircraft weight, determining the current lift and drag coefficients of the aircraft, determining currently available aircraft thrust, and estimating a currently obtainable maximum climb gradient as a function of said thrust, current weight, current lift and drag coefficients.

Abstract: The present disclosure relates to a solid-state storage device. In one arrangement, the storage device comprises a memory device comprising one of an atomic resolution storage (ARS) device and a magnetic random access memory (MRAM) device, a controller, and an integral connector that is used to directly connect the storage device to another device.

Abstract: Resistive memory elements and arrays for data storage devices are disclosed. An exemplar resistive memory element generally comprises a first conductive structure and a second conductive structure, each of the conductive structures having a width of less than 1&lgr;, anti-fuse material on each conductive structure, and conductive material on the anti-fuse material such that anti-fuse material is interposed between each conductive structure and the conductive material.

Abstract: The present invention provides several apparatus, methods, and computer program products for generating a terrain clearance floor envelope for use in a ground proximity warning system. In one embodiment, the present invention includes a processor that defines a terrain clearance floor envelope having at least two boundaries. In this embodiment, the processor defines at least one of the boundaries based on a runway position quality factor, an altitude data quality factor, and an aircraft position quality factor. Using these factors, the processor of the present invention can more precisely define the boundaries of the envelope about the selected runway. Further, the processor of the present invention does not unnecessarily increase the region between the envelope and runway where no ground proximity alarms are generated.

Abstract: A bow sight provides horizontal, vertical and at least one rotational adjustment mechanism which provides continuous movement of the sight ring without having to release a locking mechanism and still not allow unintentional movement of the sight ring. The sight has a plurality of sight pins having illuminated tips located at spaced-apart locations along a vertical sight line which extends across the sight ring. First adjustment mechanisms allow the sight pins to be rotated in order to set the location of the tips along the sight line and second adjustment mechanisms allow the sight pins to be moved along their longitudinal axes to align them with the sight line after they have been rotated. The sight also includes particular horizontal and vertical micro adjustment mechanisms which allow very small movements of the sight ring in the horizontal and vertical directions without having to release a locking mechanism.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: An apparatus, method and computer program product for suppressing an alert generated by a terrain awareness system rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.

Abstract: A terrain awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: An apparatus, system, method and computer program product to verify proper operation of an aircraft altimetry system. Aural and visual alerts may optionally be provided when a fault in the altimetry is detected.

Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.

Abstract: An electronic service transaction apparatus includes a computer peripheral device. The computer peripheral device has a communication link with an electronic service site and a messaging system operative to provide store and forward capabilities with the electronic service site. The communication link connects the computer peripheral device with the Internet. The messaging system is accessed directly by the computer peripheral device to initiate an electronic service transaction from the computer peripheral device with the electronic service site. A method is also provided.

Abstract: In a ground proximity warning system for an aircraft, a signal representing clearance of the aircraft from the underlying terrain is produced from a sea level related altitude signal and a terrain database in addition to the radio altitude signal of the aircraft's radio altimeter. An indication of reasonableness of the aircraft radio altitude signal is formed jointly responsive to the aircraft radio altitude signal and the terrain clearance signal.

Abstract: In an aircraft flight information display system, a viewing surface of the display presents an observer with a view of the flight space forward of the aircraft. The viewing surface includes a section displaying a translucent plane of flight of the aircraft along its lateral axis having as an upper bound a line transverse to the lateral axis. The portion of the flight space upward of the plane of flight of the aircraft is displayed as a second section of the flight space above the line. Information of the features of terrain in the flight space, flight parameters of the aircraft and TCAS information is processed to form images of the terrain and traffic in relation to the translucent plane of flight of the aircraft. Terrain and traffic features are rendered in different colors according to their location with respect to the plane of flight. A series of ring-like indicia are displayed in the translucent plane to indicate the distance ranges in the plane of flight of the aircraft.

Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.

Abstract: The present invention provides several apparatus, methods, and computer program products for determining a corrected distance between an aircraft and selected runway, such that the corrected distance may be used for ground proximity warning calculations. Specifically, the present invention includes a processor that receives data related to the coordinates of the aircraft and a selected runway. Based on these coordinate values, the processor determines a coordinate distance between the aircraft and selected runway. The processor also compares the altitude of the aircraft to a predetermined glideslope constructed about the runway. Specifically, the processor calculates a distance value that corresponds to the altitude of the aircraft above the runway along the predetermined glideslope. The processor compares the coordinate distance and the calculated distance values and selects either the coordinate distance or the calculated distance value as the corrected distance between the aircraft and the selected runway.

Abstract: An Internet print device font distribution method and web site. Font users are visitors to a web site that allows browsing and obtaining of fonts, either individually or in groups. Preferably, purchases are made through the web site, but the method may allow installation of fonts through the web site as a result of other authorizations, e.g., an electronic coupon for visitors or a tie-in to other products, services, and web sites. Web site functions include operating system compatibility matching. The web site obtains configuration information to insure compatibility of a font to a visitor's configuration. Software on the web site downloads, installs and configures fonts on the visitor's print device.

Abstract: The present invention provides apparatus, methods, and computer program products that monitor the altitude of an aircraft with respect to a selected runway. If the attitude of the aircraft is below a minimum glideslope with respect to the selected runway, the apparatus, methods, and computer program products of the present invention alert the flight crew, such that the altitude of the aircraft can be increased. This, in turn, increases time for reaction to abrupt changes in elevation near the selected runway. Specifically, the apparatus, methods, and computer program products of the present invention define a runway field clearance floor envelope about the selected runway that represents different preselected altitudes above the selected runway at respective distances from the selected runway. The apparatus, method, and computer program products of the present invention compare the altitude of the aircraft with respect to the selected runway to the runway field clearance floor envelope.

Abstract: A terrain-awareness system (TAS) provides LOOK-AHEAD/LOOK-DOWN as well as LOOK-UP terrain advisory and warning indications to the pilot of an aircraft of a hazardous flight condition. The TAS includes an airport data base as well as a terrain data base that is structured to provide various resolutions depending on the topography of the particular geographic area of interest. Navigational data from a satellite-based navigational system, such as a global positioning system (GPS), is used to provide a LOOK-AHEAD/LOOK-DOWN and LOOK-UP terrain advisory and terrain warning indications based upon the current position and projected flight path of the aircraft. Since the terrain advisory and the warning signals are a function of the flight path of the aircraft, nuisance warnings are minimized.

Abstract: The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current climb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second component that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach).

Abstract: A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation system. Initially, a first vertical velocity of the aircraft is determined based upon a pressure altitude value associated with the aircraft. A second vertical velocity of the aircraft is also obtained from a GPS receiver carried by the aircraft. The first and second vertical velocities are then combined to determine the vertical speed of the aircraft. In this regard, the first and second vertical velocities are combined by complimentarily filtering the first and second vertical velocities. More particularly, the first vertical velocity is typically low pass filtered to remove high frequency noise that is attributable to the relatively low resolution of the first vertical velocity value.