Robert G Gruber

US Patent:

47667249, Aug 30, 1988

Filed:

Jun 10, 1987

Appl. No.:

7/060200

Inventors:

Robert P. Gruber - North Olmsted OH

Assignee:

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

International Classification:

F02K 1100

US Classification:

602031

Abstract:

A dc power supply for spacecraft arcjet thrusters has an integral automatic starting circuit and an output averaging inductor. The output averaging inductor, in series with the load, provides instantaneous current control, and ignition pulse and an isolated signal proportional to the arc voltage. A pulse width modulated converter, close loop configured, is also incorporated to give fast response output current control.

US Patent:

41752490, Nov 20, 1979

Filed:

Jun 19, 1978

Appl. No.:

5/916655

Inventors:

Robert P. Gruber - North Olmsted OH

Assignee:

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

International Classification:

H02J 734
G05F 162

US Classification:

323 15

Abstract:

A self-reconfiguring solar cell array wherein some of the cells are switched so that they can be either in series or in shunt within the array. This feature of series or parallel switching of cells allows the array to match the load to achieve maximum power transfer. Automatic control is used to determine the conditions for maximum power operation and to switch the array into the appropriate configuration necessary to transfer maximum power to the load.

US Patent:

44647107, Aug 7, 1984

Filed:

Apr 14, 1982

Appl. No.:

6/368188

Inventors:

Robert P. Gruber - North Olmsted OH

Assignee:

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

International Classification:

H02M 3335

US Classification:

363 22

Abstract:

A d-c to d-c converter which can start with a shorted output and which regulates output voltage and current is disclosed. Voltage controlled switches directed current through the primary of a transformer the secondary of which includes virtual reactance. The switching frequency of the switches is appropriately varied to increase the voltage drop across the virtual reactance in the secondary winding to which there is connected a low impedance load. A starting circuit suitable for voltage switching devices is provided.

US Patent:

41433149, Mar 6, 1979

Filed:

Mar 29, 1978

Appl. No.:

5/891370

Inventors:

Robert P. Gruber - North Olmsted OH

Assignee:

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

International Classification:

H02J 700
G05F 146

US Classification:

323 15

Abstract:

A solar array-ion thruster system including a power control circuit which provides for use of the thruster itself in operating the solar array at the maximum power point. The power control circuit is connected between the solar array and the ion thruster and receives voltage and current signals from the former. The control circuit multiplies the voltage and current signals together to produce a power signal which is differentiated with respect to time. The differentiator output is detected by a zero crossing detector and, after suitable shaping, the detector output is phase compared with a clock in a phase demodulator. An integrator receives no output from the phase demodulator when the operating point is at the maximum power point but is driven toward the maximum power point for non-optimum operation. A ramp generator provides minor variations in the beam current reference signal produced by the integrator in order to obtain the first derivative of power.