Abstract: A reluctance motor/generator system in which a winding failure event in one channel of a multiple channel multiple phased stator assembly is accommodated by removal of the failed winding from the reluctance motor/generator machine's electrical circuit using electrical switching and an acceptance of reduced machine output capability. This electrical switching also accomplishes a reversal of magnetic polarity in poles of one remaining normal channel of the machine. The magnetic polarity reversal as accomplished electrically largely excludes secondary magnetic flux from stator poles carrying the failed winding and its associated phase windings of the channel and thereby precludes electrical energy generation in the failure event pole. In the thus achieved channel-removed mode of machine operation, a different more elongated magnetic flux path through the machine rotor and stator elements becomes active and provides reduced but usable electrical output from the machine.

Abstract: An open loop control arrangement for an electrical energy flow-controlling circuit coupling the varying terminal voltage of an energy storing capacitor to a fixed voltage direct current aircraft energy supply bus in order to supplement bus voltage transients. The open loop control arrangement allows energy flow from the varying terminal voltage of the capacitor to the fixed bus voltage by providing a time varying pulse modulation cycle in an energy conveying and voltage changing inductive element located in the energy coupling path. The open loop control arrangement senses input voltage rather than output voltage of the coupling circuit in what is termed a "feed forward " output regulation algorithm. A transistorized and integrated circuit inclusive preferred embodiment of the invention is disclosed in which a disconnect of the inductance from the aircraft supply bus is accomplished during shunt path inductance energy charging portions of an operating cycle.

Abstract: An aircraft electrical energy supply bus supplementing arrangement based on large capacitor or super capacitor storage of electrical energy for bus supplementation. Supplying of bus energy to the large capacitor is addressed in the invention. In this supplying energy is removed from the aircraft bus during quiescent conditions under the control of a energy coupling circuit which has a plurality of different energy removal rates, rates which are selected in response to the yet needed amount of capacitor charging and in a time-constant-controlled manner. Feedback control of this charging time constant selection is employed along with passive electrical device dissipation of major fractions of the time constant apparatus energy losses.

Abstract: An aircraft electrical supply bus supplementing arrangement in which electrical energy is stored in a large capacitor and energy flow between the capacitor and the bus is controlled by a bi-directional electrical converter circuit of the switched inductance type. The varying terminal voltage of the energy storing capacitor, a super capacitor, is coupled to the relatively fixed voltage of the aircraft supply bus by way of the voltage changing capability of the converter circuit switched inductance. Current flow levels in this inductance are controlled with a negative feedback regulator circuit. Energy storage efficiency in the converter is enhanced with respect to weight and physical size of the capacitor element by ability of the converter circuit to accept a widely varying input voltage while generating a relatively constant output voltage.