Abstract: A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.

Abstract: A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.

Abstract: Systems and methods for improving the presentation of wake turbulence information. A processor located on an ownship receives position, heading and type information of another aircraft and position and heading information of the ownship. The processor determines if a possible wake condition exists from the other aircraft based on at least a portion of the received information and at least one predefined threshold and generates a wake icon if a wake condition is determined to exist. The wake condition exists when the ownship's altitude is below a first threshold altitude and above a second threshold altitude, wherein the first and second threshold altitudes are based on the other aircraft's altitude.

Abstract: Systems and methods for improving the presentation of wake turbulence information. A processor located on an ownship receives position, heading and type information of another aircraft and position and heading information of the ownship. The processor determines if a possible wake condition exists from the other aircraft based on at least a portion of the received information and at least one predefined threshold and generates a wake icon if a wake condition is determined to exist. The wake condition exists when the ownship's altitude is below a first threshold altitude and above a second threshold altitude, wherein the first and second threshold altitudes are based on the other aircraft's altitude.

Abstract: A processor, software code, and a method for generating warning indicating that flaps are not suitably in a take-off position. A first component is configured to receive a first signal indicative of one of a group of flaps positions, the group including a take-off position. A second component is configured to receive a second signal indicative of an aircraft position. A third component is configured to compare the aircraft position to the contents of a database and to, by the comparison, determine whether the aircraft position is within a runway perimeter. A fourth component is configured to generate an alarm when the aircraft is within the runway perimeter and the flaps position is not the take-off position.

Abstract: In an aircraft ground proximity warning system that compares the rate of descent of an aircraft with its altitude above the terrain and in response thereto generates a warning signal when the aircraft's sink rate exceeds a predetermined limit for a particular altitude, a first type of advisory voice warning is generated for combinations of lesser descent rates and greater altitudes and a second type of imperative voice warning is generated for greater sink rates at lower altitudes where the danger of the aircraft impact with the terrain is more significant. In addition, the repetition rate of the advisory warning is increased as a function of increasing descent rate and the amplitude of the advisory warning can similarly be increased as function of increasing descent rate in order to call attention to an increasing undesirable operating condition.

Abstract: By utilizing a radio altimeter in conjunction with a measure of the aircraft speed, landing gear position and flap position, an aircraft terrain warning system is made possible which provides a voice warning indicating that the aircraft is too low with respect to the terrain when the aircraft is above a predetermined speed. For aircraft speeds below the predetermined speed, a voice warning is provided when the aircraft is below a predetermined altitude with the landing gear up indicating that the aircraft is too low with the gear up and when the gear is down and the flaps are not in a landing position and the aircraft descends below a second predetermined altitude a voice warning is generated indicating that the aircraft is too low with flaps up.

Abstract: An aircraft instrument for warning the pilot that the aircraft is in an unsafe condition in proximity to the ground. The instrument has inputs representing aircraft configuration, flight condition with respect to the ground, and glide slope. Detector circuits process the inputs and give a warning of unsafe proximity to the ground. The boundary conditions for the warning are selected to avoid false warnings. A glide slope detector distinguishes between a valid glide slope signal and spurious signals, without need for pilot input.

Abstract: In an aircraft terrain warning system utilizing a radar altimeter wherein the rate of closure to the terrain is compared with the aircraft's altitude above the terrain to generate a warning signal when the closure rate is excessive for a particular altitude, the closure rate signal is limited and biased depending upon the aircraft's closure rate and configuration in order to significantly increase the time response of the system while at the same time reducing nuisance warnings. The amplitude limit on the closure rate signal is varied, above a predefined altitude, as a function of the closure rate signal in order to provide increased warning times at greater closure rates. Circuitry, responsive to the aircraft's flap positions, is also provided to alter the characteristics of rate limiter so as to provide warning parameters that more accurately reflect operating conditions at lower aircraft speeds.

Abstract: By using air speed as an input to a ground proximity warning system that includes: a signal representative of the time rate of change of the aircraft altitude with respect to ground; circuitry for limiting the amplitude of this signal; a signal that represents a time rate of change of the aircraft's barometric altitude; and circuitry for combining the amplitude limited signal, representing the time rate of change of the aircraft with respect to ground, with a signal that represents the aircraft's altitude over ground; the effective warning time is extended by increasing the allowable amplitude, of the signal representing rate of change of the aircraft with respect to the ground, in response to the speed of the aircraft.

Abstract: In a system that compares the rate of descent of an aircraft with its altitude above ground and generates a warning signal when the sink rate exceeds a predetermined limit for a particular altitude, the maximum warning time is limited to a specified value in order to minimize nuisance warnings at higher altitudes. At a descent rate above a certain value, the excessive sink rate warning signal is inhibited for combinations of descent rates and aircraft altitudes which would provide a warning greater than a selected time to impact, such as 30 seconds.

Abstract: For use in an aircraft warning system which measures the descent below a radio glideslope and compares it with the aircraft's altitude above ground to generate a warning when the descent below glideslope exceeds predefined limits for a particular altitude, circuitry is provided to generate an advisory warning above a predefined altitude and a hard warning, or command to take immediate action, below the predetermined altitude.

Abstract: In a warning system for aircraft that generates a warning signal when the aircraft is descending during a take-off or missed approach phase of operation, the warning is inhibited for a predetermined loss of altitude in order to allow the aircraft to descend a short distance without triggering a nuisance warning. Specifically, a circuit is provided to integrate a signal representing the aircraft's rate of descent until the integrated signal is equal to a predetermined drop in altitude whereupon the warning signal is triggered.

Abstract: An aircraft instrument for warning the pilot that the aircraft is in an unsafe condition in proximity to the ground. The instrument has inputs representing aircraft configuration, flight condition with respect to the ground, and glide slope. Detector circuits process the inputs and give a warning of unsafe proximity to the ground. The boundary conditions for the warning are selected to avoid false warnings. A glide slope detector distinguishes between a valid glide slope signal and spurious signals, without need for pilot input.

Abstract: An aircraft instrument for warning the pilot that the aircraft is in an unsafe condition in proximity to the ground. The instrument has inputs representing aircraft configuration, flight condition with respect to the ground, and glide slope. Detector circuits process the inputs and give a warning of unsafe proximity to the ground. The boundary conditions for the warning are selected to avoid false warnings. A glide slope detector distinguishes between a valid glide slope signal and spurious signals, without need for pilot input.

Abstract: In an aircraft terrain warning system utilizing a radar altimeter wherein the rate of closure to the terrain is compared with the aircraft's altitude above the terrain to generate a warning signal when the closure rate is excessive for a particular altitude, the closure rate signal is limited and biased depending upon the aircraft's closure rate and configuration in order to significantly increase the time response of the system while at the same time reducing nuisance warnings. The amplitude limit on the closure rate signal, is varied, above a predefined altitude, as a function of the closure rate signal in oreder to provide increased warning times at greater closure rates. Circuitry, responsive to the aircraft's flap positions, is also provided to alter the characteristics of rate limiter so as to provide warning parameters that more accurately reflect operating conditions at lower aircraft speeds.

Abstract: In a terrain warning system wherein the rate of the aircraft's closure to the terrain is compared to the aircraft's altitude above the terrain in order to generate a warning signal for excessive closure rates, a circuit is provided to inhibit the warning signal when the aircraft begins to climb in response to the warning signal and to measure the altitude gained by the aircraft resulting in the reactivation of the warning signal if the aircraft has leveled off before gaining a predetermined amount of altitude. The circuit includes: a memory element to indicate that a warning signal has been generated; a circuit to generate a climb signal in response to a barometric rate of change signal indicating the aircraft is climbing; and an integrating circuit responsive to the barometric rate signal to determine the amount of altitude the aircraft has gained while climbing.