Braking control assembly for an aircraft gas turbine engine and method of using same

An assembly for a gas turbine engine of an aircraft, the assembly comprising:

• a rotational assembly;
• a starter generator coupled with the rotational assembly, the starter generator is configured to selectively drive rotation of the rotational assembly, and the starter generator includes a motor winding including a first electrical terminal and a second electrical terminal;
• a control relay including a variable resistor and a switch, the switch electrically connected to the first electrical terminal, the switch is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal is electrically isolated from the second electrical terminal through the switch, and in the second contact position, the first electrical terminal is electrically connected to the second electrical terminal through the switch such that a closed electrical circuit is formed through the motor winding, the first electrical terminal, the switch, and the second electrical terminal, and in the second contact position, the variable resistor is configured to selectively vary an electrical resistance between the first electrical terminal and the second electrical terminal;
• the starter generator further configured to resist rotation of the rotational assembly with the switch in the second contact position;
• and
• a controller connected in communication with the control relay, the controller includes a processor in communication with a non-transitory memory storing instructions, the storing instructions, when executed by the processor, cause the processor to:
• control the control relay to position the switch in the first contact position or the second contact position;
• and
• control the variable resistor to control the electrical resistance between the first electrical terminal and the second electrical terminal.