| 摘要 |
A control for an aircraft electrical generating and distribution system utilizes a plurality of interconnected microprocessors and comprises two engine-driven generators 15, 16 and an auxiliary power unit generator 26 with loads 20, 21 connected to the generators through circuit breakers 18, 19. A distribution bus 22 connected through tie breakers 23, 24, 27 interconnects the loads 20, 21 end the auxiliary generator 26 so that any one generator can power either or both loads. Each generator has a microprocessor control unit 30, 31, 32 responsive to the associated generator conditions to control generator operation. A microprocessor bus power control unit 42 is responsive to distribution circuit conditions and correlates information from the control units 30, 31, 32, to control the tie breakers and distribution of power from the generators to the loads. Serial data links between the control unit 42 and each control unit 30, 31, 32 provides for communication of input and control information and enables comparison of redundant circuit information enhancing reliability of the system operation. A generator voltage regulator uses the generator microprocessor control unit to develop an error voltage which is added to the average generator phase voltage, controlling the current. If phase failure occurs the control unit senses an abnormally high phase voltage, disables the average phase voltage circuit and the regulator continues to operate with the error voltage. <IMAGE> |
