Electrical lockout system for aircraft propulsion system

A propulsion system for an aircraft, comprising:

• a turbine engine including a compressor section, a combustor section and a turbine section;
• an electrical system comprising a plurality of electrical components arranged with the turbine engine, the electrical system configured to receive electrical power from an electrical power source onboard the aircraft;
• a housing structure at least partially surrounding the turbine engine, the housing structure comprising an access structure covering a portion of the turbine engine with access to the electrical system, and the access structure configured in a first position for propulsion system operation, wherein the access structure is configured to be moved from the first position for propulsion system maintenance and/or propulsion system inspection;
• and
• a lockout system configured to trigger electric decoupling of the electrical power source from the electrical system when the access structure moves away from the first position to uncover th portion of the turbine engine with access to the electrical system.

An open rotor propulsion system for an aircraft, comprising:

• a turbine engine including a compressor section, a combustor section and a turbine section;
• an electrical system comprising an electrical component arranged with the turbine engine, the electrical system configured to direct electrical power from an electrical power source onboard the aircraft to the electrical component at least during propulsion system operation;
• a housing structure at least partially housing the turbine engine, the housing structure comprising an access structure covering a portion of the turbine engine with access to the electrical system, and the access structure configured in a first position for the propulsion system operation, wherein the access structure is configured to be moved from the first position for propulsion system maintenance and/or propulsion system inspection;
• one or more switches electrically coupled between the electrical power source and the electrical system and configured to electrically couple the electrical power source to the electrical system during operation of the open rotor propulsion system;
• and
• a lockout system configured to open the one or more switches to electrically decouple the electrical power source from the electrical system when the access structure is disposed out of the first position to uncover the portion of the turbine engine with access to the electrical system.