POWER MANAGEMENT SYSTEMS FOR ELECTRICALLY DISTRIBUTED YAW CONTROL SYSTEMS

An electrically distributed yaw control system (24; 102; 202, 250; 302; 402; 502; 602) for a helicopter (10; 100; 200, 264; 300; 400; 500; 600) having a tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a power system (58; 522) includes one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) including a motor (42b, 44b, 46b, 48b; 612a, 614a, 616a, 618a) rotatably coupled to the tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a power distribution unit (534, 564). The power distribution unit (534, 564) includes a power management monitoring module (72a; 538) configured to monitor one or more flight parameters of the helicopter (10; 100; 200, 264; 300; 400; 500; 600) and a power management command module (72b; 540) configured to allocate power between the power system (58; 522) and the one or more tail rotor motors (42b, 44b, 46b, 48b; 612a, 614a, 616a, 618a) based on the one or more flight parameters of the helicopter (10; 100; 200, 264; 300; 400; 500; 600).