Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Abstract: An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.

Abstract: A collision warning method includes receiving a collision risk indication from a traffic collision avoidance system of an aircraft, receiving a preset altitude, comparing the preset altitude and an altitude associated with the collision risk indication, and providing a warning in the aircraft when the preset altitude and the altitude associated with the collision risk are within a threshold.

Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Abstract: An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.

Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Abstract: An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.

Abstract: An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.

Abstract: A system for safely landing an aircraft including a low range radio altimeter, a barometric altimeter, and an autothrottle control. The low range radio altimeter calculates a first height of the aircraft above ground-level, the barometric altimeter calculates a second height of the aircraft above ground-level, and the autothrottle control determines if the first height and the second height do not correlate. If the first and second heights are determined to lack correlation, then automatic thrust-control of the aircraft is stopped. In some embodiments, the second height is partially calculated by accessing a ground elevation database to obtain an elevation of the ground above sea level and determining a difference between the elevation of the ground above sea level and an elevation of the aircraft above sea level.

Abstract: A power line warning system for a helicopter, comprising a positioning system operable to determine the coordinates of the helicopter, an obstacle coordinate database comprising the coordinates of at least a portion of a first power line, a sensor operable to detect electromagnetic radiation from the first power line, and a visual display operable to represent a position of the first power line relative to the helicopter is described. When the coordinates of the first power line are within a predetermined distance of the coordinates of the helicopter, wherein the representation of the position of the first power line is modified when the sensor detects electromagnetic radiation from the first power line.

Abstract: A power line warning system for a helicopter, comprising a positioning system operable to determine the coordinates of the helicopter, an obstacle coordinate database comprising the coordinates of at least a portion of a first power line, a sensor operable to detect electromagnetic radiation from the first power line, and a visual display operable to represent a position of the first power line relative to the helicopter is described. When the coordinates of the first power line are within a predetermined distance of the coordinates of the helicopter, wherein the representation of the position of the first power line is modified when the sensor detects electromagnetic radiation from the first power line.

Abstract: A method and apparatus for aiding pilots in aerial refueling comprises a primary auto-throttling system (ATS) disposed in a primary aircraft and a secondary ATS disposed in a secondary aircraft. The primary ATS includes logic which generates and transmits an anticipatory signal to the secondary ATS. Based upon the received anticipatory signal, the secondary ATS automatically controls a throttle of the secondary aircraft so as to maintain an airspeed of the primary aircraft. The anticipatory signals include rate of change information including at least one of rate of change of airspeed of the primary aircraft, rate of change of pitch of the primary aircraft, and rate of change of weight of the primary aircraft.

Abstract: An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: A throttle control system that is compensated for mountain wave conditions includes an auto throttle computer and a detector for detecting the pitch or pitch angle of the aircraft. The computer is used for determining the rate of change of pitch i.e. the first derivative of pitch angle and the rate of change of the rate of change of pitch i.e. the second derivative for generating a signal indicative of the rate of change of the rate of change of pitch. The signal from the auto throttle computer is combined with the signal from the signal indicative of the second derivative to produce a combined signal which is fed to a servo assemble and motor for adjusting the throttle of an aircraft.

Abstract: An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.

Abstract: An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.

Abstract: An aircraft's brake temperature monitoring system for determining when the brake has cooled sufficiently for a safe take-off includes an aircraft brake and a temperature sensor for measuring the temperature of the brake. The system also includes a timer and indicator for indicating the brake temperatures at two different times. A computer or circuit for calculating the rate of cooling is provided and determines the time until the brakes reach a preselected temperature. An electronically stored temperature profile and ambient temperature sensor are also provided.