FRANK JOSEPH NOLA
Architects at Jefferson St, Huntsville, AL

4404511, Sep 13, 1983

Oct 13, 1981

6/310714

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 126

318729

A power factor type motor controller in which the conventional power factor constant voltage command signal is replaced during a starting interval with a graduated control voltage. The present invention adds to the three-phase system of pending application Ser. No. 199,765, filed Oct. 23, 1980, means for modifying the operation of the system for a motor start-up interval of 5 to 30 seconds. The modification is that of providing via ramp generator 174 an initial ramp-like signal which replaces a constant power factor signal supplied by potentiometer 70. The ramp-like signal is applied to terminal 40 where it is summed with an operating power factor signal from phase detectors 32, 34, and 36 to thereby obtain a control signal for ultimately controlling SCR devices 12, 14, and 16 to effect a gradual turn-on of motor 10. The significant difference of the present invention over prior art is that the SCR devices are turned on at an advancing rate with time responsive to the combination signal described rather than simply a function of a ramp-like signal alone. The added signal, the operating power factor signal, enables the production of a control signal which effectively eliminates a prior problem with many motor starting circuits, which is that of accompanying motor instabilities.

4644234, Feb 17, 1987

Sep 13, 1985

6/775548

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 602

318254

A control circuit is provided for a brushless three-phase d. c. motor which affords four quadrant control from a single command. The control circuit provides acceleration of the motor in both clockwise and counterclockwise directions and braking and generation in both clockwise and counterclockwise directions. In addition to turning on individual transistors of the transistor pairs connected to the phase windings of the motor for 120. degree. periods while the other transistor of that pair is off, the control circuit also provides, in a further mode of operation, turning the two transistors of each pair on and off alternately at a phase modulation frequency during such a 120. degree. period. A feedback signal is derived which is proportional to the motor current and which has a polarity consistent with the command signal, such that negative feedback results.

4388585, Jun 14, 1983

Mar 16, 1981

6/243683

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 900

322 47

A power generating system for adjustably coupling an induction motor, as a generator, to an A. C. power line wherein the motor and power line are connected through a triac. The triac is regulated to normally turn "on" at a relatively late point in each half cycle of its operation, whereby at less than operating speed, and thus when the induction motor functions as a motor rather than as a generator, power consumption from the line is substantially reduced.

4473792, Sep 25, 1984

Mar 31, 1983

6/481086

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 900

322 47

A coupling system for an induction motor type generator (10) to an A. C. power line (18) wherein an electronic switch means (28) which is controlled by a control system (30) is regulated to turn "on" at a relatively late point in each half cycle of its operation whereby the energizing power supplied by the line (18) to the induction motor type generator (10) is decreased and the net power delivered to the line is increased.

4417190, Nov 22, 1983

Feb 19, 1982

6/350472

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 540

318729

A control circuit for an induction motor powered system wherein a power factor controlled servo loop is used to control, via the phase angle of firing of a triac (16), the power input to the motor (14) as a function of load placed on the motor (14) by machinery of the powered system. Then, upon application of torque by this machinery to the motor (14), which tends to overspeed the motor, the firing angle of the triac (16) is automatically set to a fixed, and relatively short, firing angle.

4439718, Mar 27, 1984

Aug 28, 1981

6/297524

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 540

318729

A motor power control of the type which functions by controlling the power factor wherein one of the parameters of power factor current "on" time is determined by the "on" time of a triac through which current is supplied to the motor, and wherein, by means of a positive feedback circuit, a wider range of control is effected.

4400657, Aug 23, 1983

Nov 30, 1981

6/325886

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 540

318798

A failure detector is provided for detecting unidirectional failures in triacs, particularly as used in power factor controllers for induction motors. In a first embodiment, the triac voltage waveform is sensed and upon detection of an unbalanced signal, corresponding to failure of the triac in either the positive or negative direction, the triac is turned full on in both directions. In a second embodiment, a pair of pulsed signals are derived, the pulse durations of which are proportional to the phase difference between the load current and voltage for each half cycle, and the triac is turned full on responsive to a difference in pulse duration between the half cycle signals. An unidirectional open circuit detector is adapted to use a signal from either of the first and second embodiments to turn the triac off in response to an open circuit failure in either direction.

4489243, Dec 18, 1984

May 6, 1982

6/375684

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02P 780

307 64

A solar powered system wherein a load such as a compressor (16) is driven by a main induction motor (14) powered by a solar array (10), and an auxiliary motor (18) shares the load with the solar powered motor in proportion to the amount of sunlight available, is provided with a power factor controller (20) for controlling voltage applied to the auxiliary motor in accordance with the loading on that motor. In one embodiment, when sufficient power is available from the solar cell array the auxiliary motor is driven as a generator by excess power from the main motor so as to return electrical energy to the power company utility lines.

4266177, May 5, 1981

Jun 1, 1979

6/044431

Frank J. Nola - Huntsville AL

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

H02K 1704, H02P 540

318810

A power control circuit for an induction motor wherein a servo loop is used to control power input by controlling the power factor of motor operation, and wherein the power factor is measured by summing the voltage and current derived square wave signals.