Abstract: An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition.

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: A system and methods to record a configuration record for components of an asset is provided. The system includes a user interface device comprising a screen having a plurality of attributes and a plurality of link hotspots coupled to the plurality of attributes. A database is coupled to the user interface device, wherein the database includes an aspect associated with each of the plurality of attributes. The system includes a processor coupled to the user interface device and the database, wherein the processor configured to couple the aspect to the plurality of link hotspots.

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: An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount.

Abstract: An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition.

Abstract: A controller for determining when icing conditions are present on an outside surface of an aircraft may include a first input receiving a moisture condition on a windshield of the aircraft, a second input receiving an outside temperature, and an output that provides an icing condition determined as a function of the first input and the second input. The moisture condition can be provided by a moisture sensor positioned on an interior surface of the windshield and the windshield may include a heating system.

Abstract: A system and methods to record a configuration record for components of an asset is provided. The system includes a user interface device comprising a screen having a plurality of attributes and a plurality of link hotspots coupled to the plurality of attributes. A database is coupled to the user interface device, wherein the database includes an aspect associated with each of the plurality of attributes. The system includes a processor coupled to the user interface device and the database, wherein the processor configured to couple the aspect to the plurality of link hotspots.

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: 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: A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.

Abstract: A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.

Abstract: A helicopter speed display for displaying the maximum speed of a helicopter under current conditions is disclosed. The display includes a first scale indicative of the actual airspeed of a helicopter and a second scale juxtapositioned on the first scale for displaying a maximum airspeed under current conditions of altitude, temperature and weight in order to avoid retreating blade stall.

Abstract: A tactile warning system for warning a helicopter pilot of a pre-selected altitude during a landing maneuver includes a collective control arm for control of the aircraft and a tactile warning device operatively connected to the collective control arm. The system includes a radio altimeter for sensing the actual altitude, a computer and keyboard for inputting a pre-selected height above the ground into the computer memory. A signal generator generates a signal indicative of the actual altitude as the aircraft approaches the ground. Then, when the actual altitude is equal to or less then the pre-selected altitude the system activates the tactile device. The warning system indicative of reaching a pre-selected height is also combined with a tactile warning system for avoiding “hot starts” and for avoiding other dangerous conditions.

Abstract: A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.

Abstract: A tactile warning system for warning a helicopter pilot of a pre-selected altitude during a landing maneuver includes a collective control arm for control of the aircraft and a tactile warning device operatively connected to the collective control arm. The system includes a radio altimeter for sensing the actual altitude, a computer and keyboard for inputting a pre-selected height above the ground into the computer memory. A signal generator generates a signal indicative of the actual altitude as the aircraft approaches the ground. Then, when the actual altitude is equal to or less then the pre-selected altitude the system activates the tactile device. The warning system indicative of reaching a pre-selected height is also combined with a tactile warning system for avoiding “hot starts” and for avoiding other dangerous conditions.

Abstract: A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.