Dihydrogen supply system for an aircraft engine

A supply system for an aircraft, having a first and a second dihydrogen tank and an engine, the supply system comprising:

• a supply module comprising a first outlet pipe, a second outlet pipe, a first feed pipe fitted with a first main pump and configured to be fluidically connected to the first tank, a second supply pipe fitted with a second main pump and configured to be fluidically connected to the second tank, and means designed to channel the dihydrogen in the first and second feed pipes alternatively towards the first outlet pipe, or the second outlet pipe or both,
• a first heater,
• a second heater,
• a distribution module comprising a first introduction pipe fluidically connected to the first outlet pipe via the first heater, a second introduction pipe fluidically connected to the second outlet pipe via the second heater, a first distribution pipe and a second distribution pipe that is configured to be fluidically connected to the engine, and means for channeling the dihydrogen in the first and second introduction pipes alternatively towards the first distribution pipe or the second distribution pipe or both,
• detection means configured to detect an incident in the supply module, the distribution module, the first and second heaters, or any combination thereof, and to provide information representative of the incident that was detected, and
• a control unit configured to command the means of the supply module, the means of the distribution module, or both depending on the information provided by the detection means.