ROBERT P NELSON, M.D.
Medical Practice at Barnhill Dr, Indianapolis, IN

3930366, Jan 6, 1976

Jul 17, 1974

5/489263

Robert E. Nelson - Indianapolis IN

General Motors Corporation - Detroit MI

F02C 908

60 3915

A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories. The operation of the power plant is normally controlled by the pilot through condition levers and switches on a control quadrant, through a pitch control by which the collective pitch of the rotor blades is controlled, and through a master beeper switch which is operable to trim the setting of an isochronous governor for the rotor system and the gas generator governors. The condition lever of each engine transmits a speed command signal through the electronic control of each power unit to its gas generator governor. A signal of collective pitch transmitted from the rotor control system to each engine electronic control is another factor in setting the governor.

3963372, Jun 15, 1976

Jan 17, 1975

5/541797

Richard D. McLain - Indianapolis IN
Robert E. Nelson - Indianapolis IN
Bernard H. Van Sickle - Indianapolis IN
Oran A. Watts - Indianapolis IN

General Motors Corporation - Detroit MI

B64C 1144

416 30

A control system for a helicopter power plant with three power units driving the lifting rotor system. Each power unit comprises a gas-coupled gas turbine engine, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor, an engine electronic control, and engine accessories. Power plant operation is normally controlled by the pilot through condition levers and switches on a control quadrant, through a collective pitch control for the rotor blades, and through a master beeper switch which is operable to trim the setting of a rotor speed governor and the gas generator governors. A condition lever transmits a speed command signal through the electronic control of each power unit to its gas generator governor. A collective pitch signal from the rotor control system is another factor in setting the gas generator governor of each unit. The power plant includes a power management control which equalizes the power outputs of the engines and includes the rotor isochronous governor.

3938320, Feb 17, 1976

Jul 17, 1974

5/489264

Robert E. Nelson - Indianapolis IN

General Motors Corporation - Detroit MI

F02C 726, F02C 904

60 3914

A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories. The operation of the power plant is normally controlled by the pilot through condition levers and switches on a control quadrant, through a pitch control by which the collective pitch of the rotor blades is controlled, and through a master beeper switch which is operable to trim the setting of an isochronous governor for the rotor system and the gas generator governors. The condition lever of each engine transmits a speed command signal through the electronic control of each power unit to its gas generator governor. A signal of collective pitch transmitted from the rotor control system to each engine electronic control is another factor in setting the governor.

4236115, Nov 25, 1980

Nov 9, 1978

5/959343

Robert E. Nelson - Indianapolis IN

General Motors Corporation - Detroit MI

H03D 1300

328133

A two input flip-flop circuit is successively triggered to alternate states by two series of electrical signal pulses, each of which corresponds to one of two rotating members and is of a frequency proportional to the rotational speed of the corresponding rotating member. The flip-flop circuit output signals are applied to an averaging filter circuit that produces an output ramp signal that increases substantially linearly in amplitude as a function of change of phase displacement of the pulses of the two series of electrical signal pulses and remains at a constant value when the phase displacement of the pulses of the two series of electrical signal pulses remains constant thereby indicating an equality of the rotational speeds of the two rotating members.

4044551, Aug 30, 1977

Apr 30, 1976

5/681782

Robert E. Nelson - Indianapolis IN
Keith A. Pieper - Brownsburg IN

General Motors Corporation - Detroit MI

F02C 726

60 3914

A stagnation sensing control for determining when a gas turbine engine has stagnated during a start phase of operation includes means for sampling the engine speed at a first predetermined point in time and means to hold the sampled speed in memory and further including means operative following a period of time to compare engine speed at the later point in time with the speed in memory and means operative if the speed increase is less than an established amount greater than the sampled speed in memory to produce an engine shutdown signal to operate engine starter and shut down circuits for terminating engine operation.

3969890, Jul 20, 1976

Jul 17, 1974

5/489262

Robert E. Nelson - Indianapolis IN

General Motors Corporation - Detroit MI

F02C 702

60 3915

A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories.