A contra-rotating aircraft propulsion system with an electrical power generation apparatus comprising: a first shaft; a first rotor blade set mounted to said first shaft and configured to propel the aircraft; a first winding mounted to said first shaft; a first electrical load, being a first de-icing element of the first rotor blade set, mounted to said first shaft and electrically connected to receive electrical current from said winding; a second shaft; a second rotor blade set mounted to said second shaft and configured to propel the aircraft; and a first permanent magnet field array mounted adjacent to said first winding on said second shaft, wherein said first shaft and said second shaft are operatively connected so that the second shaft contra-rotates relative to said first shaft about a common axis, so that rotation of said first permanent magnet field array relative to said first winding induces an electrical current in said first winding to power said first electrical load, and the first rotor blade set and the second rotor blade set contra-rotate; the apparatus further comprising: a second winding mounted to said second shaft and extending toward said first shaft; a second permanent magnet field array mounted to said first shaft and adjacent to said second winding; a second electrical load, being a second de-icing element of the second rotor blade set, mounted to said second shaft and electrically connected to receive electrical current from said second winding; a first power control unit electrically connected between said first winding and said first de-icing element to modify said electrical current; and a second power control unit electrically connected between said second winding and said second de-icing element to modify said electrical current. a first shaft; a first rotor blade set mounted to said first shaft and configured to propel the aircraft; a first winding mounted to said first shaft; a first electrical load, being a first de-icing element of the first rotor blade set, mounted to said first shaft and electrically connected to receive electrical current from said winding; a second shaft; a second rotor blade set mounted to said second shaft and configured to propel the aircraft; and a first permanent magnet field array mounted adjacent to said first winding on said second shaft, wherein said first shaft and said second shaft are operatively connected so that the second shaft contra-rotates relative to said first shaft about a common axis, so that rotation of said first permanent magnet field array relative to said first winding induces an electrical current in said first winding to power said first electrical load, and the first rotor blade set and the second rotor blade set contra-rotate; the apparatus further comprising: a second winding mounted to said second shaft and extending toward said first shaft; a second permanent magnet field array mounted to said first shaft and adjacent to said second winding; a second electrical load, being a second de-icing element of the second rotor blade set, mounted to said second shaft and electrically connected to receive electrical current from said second winding; a first power control unit electrically connected between said first winding and said first de-icing element to modify said electrical current; and a second power control unit electrically connected between said second winding and said second de-icing element to modify said electrical current. a second winding mounted to said second shaft and extending toward said first shaft; a second permanent magnet field array mounted to said first shaft and adjacent to said second winding; a second electrical load, being a second de-icing element of the second rotor blade set, mounted to said second shaft and electrically connected to receive electrical current from said second winding; a first power control unit electrically connected between said first winding and said first de-icing element to modify said electrical current; and a second power control unit electrically connected between said second winding and said second de-icing element to modify said electrical current.