Wiring harness conductive shield termination arrangement
AssigneePratt & Whitney Canada Corp.
InventorsFraz Ahmad Kharal, Antwan Shenouda
Life of this patent
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Abstract
A system for transmitting an alternating current in an aircraft. The system includes a source of electricity in the aircraft having a source connector housing, an electric load in the aircraft having a load connector housing, a cable electrically coupling the source of electricity to the electric load, a shield surrounding the cable and having a first end electrically connected to the source connector housing, and a capacitor disposed inside the load connector housing and electrically coupling a second end of the shield to the load connector housing.
Claims20
A system for transmitting an alternating current in an aircraft, comprising:
- a source of electricity in the aircraft having a source connector housing;
- an electric load in the aircraft having a load connector housing;
- a cable electrically coupling the source of electricity to the electric load;
- a shield surrounding the cable and having a first end electrically connected to the source connector housing;
- and
- a capacitor disposed inside the load connector housing and electrically coupling a second end of the shield to the load connector housing.
An electric motor system for an aircraft, comprising:
- a motor controller having a motor controller connector housing;
- an electric motor having an electric motor connector housing;
- a cable electrically coupling the motor controller to the electric motor;
- and
- a shield extending from a first end to a second end, the shield surrounding the cable and grounded to the motor connector housing at the first end and to the electric motor connector housing at the second end, the shield electrically coupled to one of the motor controller connector housing and the electric motor connector housing via a capacitor disposed inside the one of the motor controller connector housing and the electric motor connector housing.
An hybrid-electric propulsion system for an aircraft, comprising:
- an air mover;
- a heat engine rotatably coupled to the air mover;
- an electric motor rotatably coupled to the air mover;
- a motor controller;
- and
- a three-phase cable assembly electrically coupling the motor controller to the electric motor, the three-phase cable assembly comprising three cables arranged in parallel, each of the three cables having a shield surrounding each of the three cable and grounded to a connector for the electric motor via a capacitor disposed in the connector for the electric motor.
Dependencies are inferred from the claim text.