Abstract: An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.

Abstract: An aircraft taxi path guidance and display system is provided. The aircraft taxi path guidance and display system includes or cooperates with at least one source of aircraft status data, and a source of airport feature data associated with an airport field. The aircraft taxi path guidance and display system includes a processor operationally coupled to the source of aircraft status data and to the source of airport feature data. In response to aircraft status data and airport feature data, the processor predicts undesired deviations from an active surface area (e.g., an excursion). The processor generates corrective action associated with the excursion, and displays symbology that is graphically representative of the corrective action.

Abstract: An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.

Abstract: An aircraft taxi path guidance and display system is provided. The aircraft taxi path guidance and display system includes or cooperates with at least one source of aircraft status data, and a source of airport feature data associated with an airport field. The aircraft taxi path guidance and display system includes a processor operationally coupled to the source of aircraft status data and to the source of airport feature data. In response to aircraft status data and airport feature data, the processor predicts undesired deviations from an active surface area (e.g., an excursion). The processor generates corrective action associated with the excursion, and displays symbology that is graphically representative of the corrective action.

Abstract: A starting system for aircraft engines employs power from multiple power sources. Each engine is started with a starter motor that is driven by the same multiple power sources which collectively provide starting power. As engine speed increases during each starting cycle a voltage boost is progressively provided by a boost converter. The starting system allows use of voltages higher than output voltage of the power sources while allowing the power sources to remain connected to a main aircraft power distribution bus.

Abstract: A starting system for aircraft engines employs power from multiple power sources. Each engine is started with a starter motor that is driven by the same multiple power sources which collectively provide starting power. As engine speed increases during each starting cycle a voltage boost is progressively provided by a boost converter. The starting system allows use of voltages higher than output voltage of the power sources while allowing the power sources to remain connected to a main aircraft power distribution bus.

Abstract: An electrical power distribution system comprises a solid state power controller in communication with an aircraft system main data bus via a gateway module and a condition based maintenance module in communication with the solid state power controller via a communication network distinct from the main data bus. A method of load/feeder health assessment for an electrical power distribution system includes applying a controlled excitation to a load; sampling information from the load/feeder system for the load; characterizing a normal behavior of the load/feeder system for the load; determining if the load characteristics are within the normal behavior profile for the load; and shutting down power to the load if load characteristics are not within the profile when immediate action is indicated or generating a health message for the load when immediate action is not required.

Abstract: A method and apparatuses are implemented for electric power systems. An apparatus for power conversion according to one embodiment comprises: a multiple function power converter (77), the multiple function power converter (77) being capable of performing functions of a static inverter, and being capable of at least one of performing functions of a motor controller, and performing functions of a start converter to use a generator as a starter. An architecture system for aircraft according to another embodiment comprises: one or more rectifiers (408), wherein the one or more rectifiers (408) receive at least one high frequency AC power input; and a plurality of power conversion devices (78) optionally connectable to drive at least one high frequency generator (105) as a starter and at least one load, the input of each power conversion device (78) being connected to at least one rectifier (408).

Abstract: The present invention provides an overload protection circuit having a first switch connected at a first side to a source of electrical power and at a second side to a load, the switch having on and off modes and a second switch connected between the first switch second side and ground, the second switch having on and off modes. A control module generates at least one signal controlling the first switch mode and the second switch mode wherein the signal turns the second switch to the off mode when turning the first switch to the on mode and the signal turning the second switch to an on mode when turning the first switch to the off mode. Both over current and leakage protection are thereby achieved.

Abstract: The present invention provides an overload protection circuit having a first switch connected at a first side to a source of electrical power and at a second side to a load, the switch having on and off modes and a second switch connected between the first switch second side and ground, the second switch having on and off modes. A control module generates at least one signal controlling the first switch mode and the second switch mode wherein the signal turns the second switch to the off mode when turning the first switch to the on mode and the signal turning the second switch to an on mode when turning the first switch to the off mode. Both over current and leakage protection are thereby achieved.

Abstract: An electrical power distribution system comprises a solid state power controller in communication with an aircraft system main data bus via a gateway module and a condition based maintenance module in communication with the solid state power controller via a communication network distinct from the main data bus. A method of load/feeder health assessment for an electrical power distribution system includes applying a controlled excitation to a load; sampling information from the load/feeder system for the load; characterizing a normal behavior of the load/feeder system for the load; determining if the load characteristics are within the normal behavior profile for the load; and shutting down power to the load if load characteristics are not within the profile when immediate action is indicated or generating a health message for the load when immediate action is not required.

Abstract: A method and apparatuses are implemented for electric power systems. An apparatus for power conversion according to one embodiment comprises: a multiple function power converter (77), the multiple function power converter (77) being capable of performing functions of a static inverter, and being capable of at least one of performing functions of a motor controller, and performing functions of a start converter to use a generator as a starter. An architecture system for aircraft according to another embodiment comprises: one or more rectifiers (408), wherein the one or more rectifiers (408) receive at least one high frequency AC power input; and a plurality of power conversion devices (78) optionally connectable to drive at least one high frequency generator (105) as a starter and at least one load, the input of each power conversion device (78) being connected to at least one rectifier (408).

Abstract: An adaptive, sensorless position sensing apparatus (250) derives rotor position of a synchronous machine (200). The apparatus (250) comprises a first rotor position deriving unit (300) for generating first rotor position values by applying a first sensorless rotor position calculation technique, which emulates a resolver; a second rotor position deriving unit (400) for generating second rotor position values by applying a second sensorless rotor position calculation technique; and a rotor position result output unit (450) for outputting rotor position results over a range of rotor speeds as a function of the first rotor position values, the second rotor position values, and rotor speed.

Abstract: A position sensing apparatus (300) derives rotor position of a synchronous machine (200) from signals output from the machine (200). In one embodiment, the position sensing apparatus (300) comprises: a bandpass filter (322) that filters phase voltage signals output from main stator windings (216) of the synchronous machine (200) during AC excitation, thereby extracting a rotor position-indicating component from the phase voltage signals; a converter (324) that converts the filtered phase voltages into balanced two-phase quadrature signals, the balanced two-phase quadrature signals indicating positioning of the rotor (212); and an excitation controller (204) for controlling AC excitation frequency as a function of rotor speed.

Abstract: An adaptive, sensorless position sensing apparatus (250) derives rotor position of a synchronous machine (200). The apparatus (250) comprises a first rotor position deriving unit (300) for generating first rotor position values by applying a first sensorless rotor position calculation technique, which emulates a resolver; a second rotor position deriving unit (400) for generating second rotor position values by applying a second sensorless rotor position calculation technique; and a rotor position result output unit (450) for outputting rotor position results over a range of rotor speeds as a function of the first rotor position values, the second rotor position values, and rotor speed.

Abstract: A position sensing apparatus (300) derives rotor position of a synchronous machine (200) from signals output from the machine (200). In one embodiment, the position sensing apparatus (300) comprises: a bandpass filter (322) that filters phase voltage signals output from main stator windings (216) of the synchronous machine (200) during AC excitation, thereby extracting a rotor position-indicating component from the phase voltage signals; a converter (324) that converts the filtered phase voltages into balanced two-phase quadrature signals, the balanced two-phase quadrature signals indicating positioning of the rotor (212); and an excitation controller (204) for controlling AC excitation frequency as a function of rotor speed.

Abstract: A position sensor emulator system and method for use in the control of synchronous machines are disclosed. The position sensor emulator system (220) includes a first bandpass filter (222) that filters phase voltage signals from a stator of a synchronous machine (230). A converter (224) that converts the filtered phase voltages into balanced two-phase quadrature signals. A rectifier (226) that rectifies exciter voltage signals of the synchronous machine (230) and a second bandpass filter (228) that filters the rectified exciter voltage signals to generate a reference signal.

Abstract: A position sensor emulator system and method for use in the control of synchronous machines are disclosed. The position sensor emulator system (220) includes a first bandpass filter (222) that filters phase voltage signals from a stator of a synchronous machine (230). A converter (224) that converts the filtered phase voltages into balanced two-phase quadrature signals. A rectifier (226) that rectifies exciter voltage signals of the synchronous machine (230) and a second bandpass filter (228) that filters the rectified exciter voltage signals to generate a reference signal.