Abstract: A process for diagnosing the proper operation of direction indicator lights of a motor vehicle includes the steps of temporally and alternately shifting the end of illumination of the right and left change of direction indicator lamps of the vehicle, measuring the current passing through a power circuit of the direction indicator lamps during the temporal shift, comparing the measured value with a reference value, and deducing therefrom whether at least one of the lamps is inoperative and in this case informing the driver thereof. A device for diagnosing the proper operation of the direction indicator lights of a motor vehicle is also provided.

Abstract: A cabin pressure altitude monitor and warning system provides a warning when a detected cabin pressure altitude has reached a predetermined level. The system is preferably embodied in a portable, pager-sized device that can be carried or worn by an individual. A microprocessor calculates the pressure altitude from signals generated by a calibrated pressure transducer and a temperature sensor that compensates for temperature variations in the signals generated by the pressure transducer. The microprocessor is programmed to generate a warning or alarm if a cabin pressure altitude exceeding a predetermined threshold is detected. Preferably, the microprocessor generates two different types of warning or alarm outputs, a first early warning or alert when a first pressure altitude is exceeded, and a second more serious alarm condition when either a second, higher pressure altitude is exceeded, or when the first pressure altitude has been exceeded for a predetermined period of time.

Abstract: A conditional TAWS algorithm system and method for providing advanced warnings of potential CFIT situation which could result from predictable errant course changes.

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: 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: The present invention includes a system, method and computer program product for reducing nuisance warnings during low altitude flight conditions and in the presence of low position uncertainty. The system includes a first component that determines whether the aircraft is in a low altitude flight condition and a second component that determines the position, positional uncertainty, and the heading. The system also includes a third component that attenuates and refines the look-ahead envelope in accord with the determined condition of flight and positional uncertainty.

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 altitude 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 system and method for determining the vertical integrity of an altitude component of an aircraft navigational signal through the use of a receiver-autonomous vertical integrity monitoring (RAVIM) algorithm. The system and methods also provide timely warning to vehicle operators if the integrity of the signal is unacceptable or unknown. The system and methods are capable of determining the vertical integrity of an incoming signal without relying upon data embedded within the incoming signal itself. In addition, the system and methods of the present invention provide vertical integrity to vehicle operators in instances, such as when the specific aircraft navigational signal is not operating, when the specific aircraft navigational signal is not available in a particular region, or when an aircraft is operating outside the geographic area covered by the specific aircraft navigational signal system.

Abstract: A method and system for conducting local neighborhood searches among three or more aircraft routes to cure any irregularity in one of the aircraft routes, in which states of Binary Operations are stored, time and space feasibility tables are created from the stored states, and Tertiary Operations responsive to data stored in the feasibility tables are performed on the three or more entities to effect a repair.

Abstract: Terrain navigation apparatus (1) for a stationary or moving vehicle (2) when the apparatus (1) is mounted thereon, including a system (3) for determining position, velocity, altitude and attitude incorporating at least six sensing means operable to provide signals indicative of a first measured height (5), a first velocity (7) and a first position (9) of the vehicle (2), scanning means (11) operable to scan terrain (13) around the vehicle (2) and measure a range (15) from the vehicle (2) thereto, first combining means (17) for combining signals indicative of the first measured height, the range and the first position (5, 15, 9) of the vehicle (2), together with error estimates (19) associated therewith, and for outputting results of said combining process, error-estimating means (21) for receiving as input signals results of said combining process and for providing said error estimates(19), such that the error-estimating means (21) and first combining means (17) operatively interact to effect terrain navigati

Abstract: The present invention provides several apparatus, methods, and computer program products for determining a look ahead distance value for use in a ground proximity warning system. Specifically, the present invention provides apparatus, methods, and computer program products that generate a candidate look ahead distance value that provides a constant reaction time for varying aircraft speeds. The apparatus of the present invention includes a processor that generates the constant reaction time look ahead distance by multiplying a desired reaction time by the speed of the aircraft. This constant reaction time look ahead distance value is compared by the processor to other candidate look ahead distance values that have variable reaction times for varying aircraft speeds. If the aircraft is traveling at a relatively high speed, the processor of the present invention selects the constant reaction time look ahead distance value for use in the ground proximity warning system.

Abstract: A method and apparatus for automatically providing advisories to pilots in a monitored airspace comprises monitoring weather conditions and air traffic in an airspace and then generating and broadcasting advisories over a radio channel in response to relevant air traffic conditions. Advisory lengths are sized based on the volume of communications on the common traffic advisory frequency. An airspace model, made up of a multitude of constantly updated records, is used to keep track of important flight information and weather conditions. A monitoring CPU, accessing the airspace model, creates the advisory messages based upon hazard criteria, guidelines, airport procedures and other relevant air traffic data.

Abstract: An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot.

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: An aircraft terrain warning generator is provided having a terrain and obstacle warning envelope having a lower boundary formed according to the lesser of the current aircraft flight path angle and the obtainable climb gradient.

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 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.

Abstract: A display system for an airplane or other vehicle is disclosed. A rear projection LCD is used to allow for a maximum amount of screen area to be used in displaying operator pertinent data.

Abstract: In order to provide the pilots with a display or a map of the terrain below the aircraft, a display is generated on a cockpit display, such as a weather radar, of the contours of the terrain below the aircraft. The terrain contour display is generated from aircraft position information, a terrain data base, and a terrain awareness envelope defined by awareness boundaries. Terrain contours are depicted with the highest terrain within the envelope colored red, high intermediate terrain contours in yellow with varying dot densities, low intermediate terrain contours in green with varying dot densities, and the lowest terrain in black. The green contours can be overwritten with a low density yellow based on a pre-caution envelope which extends certain of the awareness boundaries to provide notice to a pilot of upcoming cautions.

Abstract: A system and method for improving the accuracy of altitude determinations in an inertial navigation system. Pressure measurements available to the inertial navigation system are used to initially calculate an estimated pressure altitude using the standard day model for the atmosphere. Temperature measurements are further utilized in the physical relationship between temperature, pressure, and altitude to compute a second computed altitude. A change between subsequent second computed altitudes is calculated and compared with a respective change in the computed pressure altitude in order to generate a correction value. The correction value is then used to modify the computed pressure altitude to generate a more accurate determination of the absolute altitude of the inertial navigation system.

Abstract: An apparatus and method for automatically and independently determining aircraft altitude and alerting the pilot to deviations from a target altitude exceeding a specified tolerance. The alerter comprises an altitude sensing means for sensing the present altitude of the aircraft. The invention discloses three sources for altitude information namely, a self-contined sensor such as a pressure transducer, a Global Positioning System receive, or an altitude encoder. A target entry means is used for entering the target altitude. An indicating means signals an altitude alerting condition upon the detection of a condition wherein the absolute difference is larger than the tolerance value. The altitude alerting apparatus may also comprise a display means for display of the present aircraft altitude information.

Abstract: The present invention provides ground proximity warning system and method for aircraft, particularly rotary wing aircraft such as helicopters. The warning system generally includes an air ground detection device disposed on the aircraft to confirm whether the aircraft is on the ground or in the air. A controller is coupled to the air ground detection device and configured to move between a ground state when the aircraft is on the ground and an airborne state when the aircraft is in the air. The controller may be used for a variety of applications within the aircraft, such as disabling a ground proximity warning device when the aircraft is on the ground and enabling the warning device when the aircraft is in the air. In addition, the air ground controller may be used to signal the beginning and the end of a flight for the aircraft's flight history fault memory.

Abstract: A combined altitude and height-above-ground indicator for an aircraft enables the altitude and the height of an aircraft to be displayed simultaneously. The combined indicator includes a first sensor and a second sensor which respectively sense altitude and height above ground, means for processing the information supplied by the first and second sensors, and means for displaying the sensed altitude and height-above-ground information by superimposing the altitude and height-above-ground information on the same scale against a pointer. The scale includes a transparent first part which represents a pressure-altitude display, and a second part which is a mask positioned under the first part so that it masks the background of the indicator for altitude levels which are below the measured height above ground.

Abstract: A method of automated scan compensation in a target acquisition system for reducing areas of potential threat surrounding an aircraft. The target acquisition system is located on an aircraft and adapted to receive data from a plurality of sensors. The target acquisition system includes a scanning device with adjustable scan limits for scanning a desired area in the vicinity of the aircraft. The method involves determining the aircraft's current position, altitude, and heading. The terrain in the vicinity of the aircraft is then scanned and a line of sight between the aircraft and the scanned terrain is determined. Changes in the terrain which prevent other areas of the terrain in the vicinity of the aircraft from being scanned are also determined. The method then involves determining adjustments to the scan limits on the target acquisition system to reduce the size of the unscanned areas, and adjusting the scan limits as the aircraft flies over the terrain.

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: A combined altitude and height-above-ground indicator for an aircraft includes a first sensor and a second sensor which respectively sense altitude and height-above-ground, a processor for processing the information supplied by the first and second sensors, and a display for displaying the altitude and height-above-ground information, showing the two items of information against each other, on the same scale against at least one pointer.

Abstract: A flight warning system comprises an outside temperature probe for sensing outside temperature, a gyroscope for sensing aircraft bank angle, a static transducer for sensing static pressure, and a dynamic pressure sensor for receiving total pressure from a pitot tube. A computer is responsive to the gyroscope, static transducer, outside temperature probe and dynamic pressure sensor calculates whether the aircraft is entering a stall condition by comparing the aircraft's bank angle with the stall bank angle. The computer can also calculate whether sufficient altitude exists for the aircraft to safely return to a field after a power failure. An output device can also be provided for indicating the existence of said sufficient altitude, and a stall indicator can be provided for indicating whether the aircraft is entering a stall condition. A method for determining the existence of a stall condition with the aircraft is also disclosed.

Abstract: An integrated vertical situation display (IVSD) for an aircraft, and method of displaying vertical situation information, are disclosed herein. The IVSD includes an electronic display for displaying the vertical situation of the aircraft, input interfaces for receiving vertical profile information signals, and a processing circuit for reading the information signals and generating display signals applied to the display therefrom. The display has a vertical profile view area to display the vertical situation in front of, above, and below the aircraft. The information sources may include a flight management system, traffic alert and collision avoidance system (TCAS) and a ground proximity warning system. Vertical situations are displayed by visual indicia representing, for example, aircraft position, path angle, flight path, waypoints, TCAS targets, altitude preselect, decision height, runway, ground contour, and vertical speed.

Abstract: A terrain awareness system and method which provides increased warning times to the pilot of an aircraft of a hazardous flight condition while minimizing nuisance warnings. An important aspect of the invention is that the terrain background information as well as the terrain advisory and warning indications may be displayed on a navigational or weather display, normally existing within an aircraft, which reduces the cost of the system and obviates the need for extensive modifications to existing displays, such as a navigational and weather radar type display.

Abstract: A hazard alert device for aircraft prioritizes various alerts according to predefined criteria. The device enables more optional alerting of hazardous conditions than a system of separate independent and discrete devices.

Abstract: Aircraft tail strike protection is provided by displaying to a pilot tail strike warning symbols during takeoff and approach to landing. In a takeoff scenario, a pitch margin indicator symbol referenced to a boresight symbol provides a pilot with anticipatory information and an awareness of the pitch attitude margin before a tail strike incident. In an approach to landing scenario, a TAILSTRIKE warning annunciation is referenced to a flight path symbol and alerts the pilot of an impending tail strike incident. The symbols displayed during either scenario center on the pilot area of focus for each task. They give the pilot an awareness of an impending tail strike incident and necessary reaction time to avoid it.

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: In order to provide the pilots with a display or a map of the terrain below the aircraft, a display is generated on a cockpit display, such as a weather radar, of the contours of the terrain below the aircraft. The terrain contour display is generated from aircraft position information and a terrain data base. Terrain contours are depicted with the highest terrain colored red, intermediate terrain contours in green with varying dot densities and the lowest terrain in black.

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 engine control system for a first aircraft belonging to a family of aircraft which includes at least a second aircraft, the first aircraft having a maximum mass which is greater, within a predetermined limit, than that of the second aircraft. For an engine of the first aircraft, a first thrust command law controls a thrust of an engine of the first aircraft during take-off phase (T), and a second thrust command law, controls a thrust of the engine to correspond with a part of the thrust command laws applicable to the second aircraft during all other flight phases (R) of the first aircraft. The transition from one flight phase to another is detected to supply the engine with a control signal corresponding to one or the other of the first thrust command law or the second thrust command law.

Abstract: The present invention provides ground proximity warning system and method for aircraft, particularly rotary wing aircraft such as helicopters. The warning system generally includes an air ground detection device disposed on the aircraft to confirm whether the aircraft is on the ground or in the air. A controller is coupled to the air ground detection device and configured to move between a ground state when the aircraft is on the ground and an airborne state when the aircraft is in the air. The controller may be used for a variety of applications within the aircraft, such as disabling a ground proximity warning device when the aircraft is on the ground and enabling the warning device when the aircraft is in the air. In addition, the air ground controller may be used to signal the beginning and the end of a flight for the aircraft's flight history fault memory.

Abstract: An integrated flight safety device for general aviation aircraft includes a radio altimeter and flight data recorder.

Abstract: An apparatus and method for automatically and independently determining aircraft altitude and alerting the pilot to deviations from a target altitude exceeding a specified tolerance. The alerter comprises an altitude sensing means for sensing the present altitude of the aircraft. The invention discloses three sources for altitude information namely, a self-contined sensor such as a pressure transducer, a Global Positioning System receive, or an altitude encoder. A target entry means is used for entering the target altitude. An indicating means signals an altitude alerting condition upon the detection of a condition wherein the absolute difference is larger than the tolerance value. The altitude alerting apparatus may also comprise a display means for display of the present aircraft altitude information.

Abstract: The Aircraft Landing Gear Warning System is an electronic device designed for general aviation aircraft having retractable landing gear. The unit attaches to the aircraft. The system incorporates means of determining the aircraft's proximity to the ground and the status of the landing gear. If the device determines that the aircraft has descended to approximately 100 ft. above the ground and the wheels are retracted, the device provides a visual and audible warning to the pilot.

Abstract: A hazard alert device for aircraft prioritizes various alerts according to predefined criteria. The device enables more optional alerting of hazardous conditions than a system of separate independent and discrete devices.

Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.

Abstract: A radar based terrain and obstacle detection device for aircraft detects obstacles and terrain ahead of the aircraft. An alert is sounded if the obstacle or terrain is above a clearance plane positioned ahead of the aircraft.

Abstract: A visual display format for a terrain situational awareness system comprising a horizontal terrain elevation view and a profile terrain elevation view of potential terrain hazards integrated onto a single display.

Abstract: In a method for the piloting of an aircraft, enabling low-altitude flight by setting up a tangent with the relief to be overflown, the aircraft pilot determines the goals to be attained on a cartographic screen. This is done in enabling a computer, using altimetrical data, to define a ground profile and then a set of straight lines at a tangent to said ground profile. A method of this kind has the advantage of enabling an optimized flight plan to be reconfigured directly, when the pilot comes up against a threat that makes it necessary to change the pre-set flight plan. Application to military transport aircraft.

Abstract: A ground collision avoidance system that exhibits improved accuracy and performance by integrating with all other aircraft systems including guidance systems, navigation systems, digital terrain elevation databases, mission computers, and radar altimeters. The ground collision avoidance system fully utilizes active onboard sensors in combination with the knowledge of terrain and obstacle data contained in databases. Furthermore, the ground collision avoidance system provides a multiple processing path to determine numerous predicted flight paths based on a number of reasonable assumptions regarding the aircraft flight during a predetermined amount of time. By using predictive flight path schemes a realistic estimate of the predicted flight path envelope can be determined and then this information can be used in conjunction with accurate terrain elevation databases to determine whether a ground collision condition exists.

Abstract: A collision avoidance device for an aircraft of the type comprises means for the geographical localization of the aircraft, means for the computation, for each geographical place, of a safety floor above which the aircraft must be positioned, means to predict the position in the air of the aircraft between a first given instant and a second given instant and means to compare the predicted position in the air of the aircraft with respect to the specified security floor. The safety floor, which is used for the comparison, is consolidated beforehand by means of a sensor that detects the obstacles in a forward sector of the aircraft and provides means with measurements enabling the computation of the altitude of these obstacles with respect to a reference level. The disclosed device has the advantage of enabling a reduction in the risk of delayed alarms and harmful alarms.

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: Information, an alert or an alarm is supplied to an aircraft in proximity to the ground. A grid of geographic coordinates is established, each mesh of which exhibits a defined relief. The trajectory of the aircraft is predicted over a predetermined time interval. An intersection, if any, between the predicted trajectory and the relief of at least one of the meshes is determined. An alert or alarm is activated in the case of such an intersection. The alert or alarm is inhibited when the aircraft is in landing configuration or when the runway is detected and a series of conditions relating to landing are fulfilled.

Abstract: The present invention provides ground proximity warning system and method for aircraft, particularly rotary wing aircraft such as helicopters. The warning system generally includes a barometric altitude rate detector, such an altimeter and a rate circuit, disposed to detect the rate of change of the barometric altitude of the aircraft. A controller is coupled to the detector for receiving the barometric altitude rate signals and adjusting the signals based on the ground effect from the main rotors when the aircraft is near the ground. Typically, the controller decreases the barometric altitude rate signals to compensate for the apparent increase in barometric altitude rate caused by ground effects. This reduces the number of nuisance warnings that may otherwise occur during takeoffs, landings or other low altitude flight conditions.

Abstract: A landing gear warning system for an aircraft with at least one retractable landing gear member comprising: (a) a landing gear indicator adapted for generating a signal representative of the position of the landing gear member; (b) an aircraft positioning system adapted for generating a signal representative of the aircraft's latitude, longitude, and elevation; (c) a pilot warning device; and (d) a computer system operatively coupled to the landing gear indicator, the aircraft positioning system, and the pilot warning device, wherein the computer system includes a database that contains the longitude and latitude, and elevation of a plurality of runways, and wherein the computer system is adapted for receiving the signal representative of the aircraft's latitude, longitude, and elevation, adapted for receiving the signal representative of the position of the landing gear member, and adapted for generating a pilot warning signal that activates the pilot warning device if the aircraft's elevation is less than a