Chromalox, Inc.

Jbt Aerotech Corporation

John Bean Technologies Corporation

Oshkosh Aerotech, LLC

Steven U Nestel

Sam W Henry

Donald M Cunningham

Paul R Neilson

Randy C Jarrett

Kirk Rodney Nelson

Brent Andrew Carlson

In an embodiment, an airport electric vehicle charging system includes a current transducer electrically coupled with a power source; a solid state converter electrically coupleable with an aircraft at or near an airport gate and configured to provide and maintain power to the aircraft; and a controller. The system further includes a first feedback loop between the controller and the current transducer; a second feedback loop between the controller and the solid state converter; and a battery charger electrically coupled with the power source and configured to charge one or more electric vehicles. The first feedback loop provides a first feedback signal generated by the current transducer to the controller. The second feedback loop provides a second feedback signal generated by the solid state converter to the controller. The battery charger is configured to consume power from the power source in accordance with the first and second feedback signals.

Airport electrical power charger system for charging aircrafts and ground support equipment

Airport electric vehicle charging system

In an embodiment, an integrated ground support system for an aircraft is described herein, the system including a frame on which the system is arranged as a singular assembly. An engine, drive train, alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

Variable pneumatic output with constant electrical output driven by a single engine

A load bank, comprising a housing, a user interface located on the housing, the user interface having at least one control, and at least one heater located in the housing and controlled by the control, wherein the control configures the heater to act as a test load for testing a power source.

Compact load bank for testing power systems

An integral heating and cooling unit is disclosed. The integral heating and cooling unit controls the temperature of a working fluid by heating or cooling the fluid either independently or in tandem. The integral heating and cooling unit includes a casing or outer housing, which defines a plenum. A heat exchanger pipe is attached to the outer housing and passes through the plenum. A plurality of heating elements connects to the outer housing and extends into the plenum. The heating elements heat the working fluid when they are powered and the working fluid passes through the plenum. The heat exchanger pipe extracts heat from the working fluid when a cooling fluid passes through the pipe and in heat transfer relation with the working fluid.

Integral heating and cooling unit

Growing community of inventors

Ogden, UT, United States of America

Steven U Nestel