A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or mor
A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.
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1. A method of controlling an aircraft electrical system, the electrical system comprising: an alternating current electrical machine comprising a plurality of electrical phases, each phase having a nominal power rating, the electrical machine being configured to operate on failure of one or more ph
1. A method of controlling an aircraft electrical system, the electrical system comprising: an alternating current electrical machine comprising a plurality of electrical phases, each phase having a nominal power rating, the electrical machine being configured to operate on failure of one or more phases; the method comprising: determining a power requirement;sensing a fault of one or more phases of the electrical machine, and, where a fault is sensed:controlling the electrical machine to operate in a fault condition, in which the non-faulty phases of the electrical machine provide the electrical power requirement; anddetermining whether the power provided by the remaining non-faulty electrical phases exceeds the nominal power rating of the respective phase, and providing an overrating signal to a flight computer of the aircraft where the power provided by each phase exceeds the nominal power rating of the respective phase. 2. A method of controlling an aircraft electrical system according to claim 1, wherein the alternating current electrical machine comprises an electrical motor, and the power comprises mechanical power provided by the electrical motor. 3. A method of controlling an aircraft electrical system according to claim 2, wherein the electrical motor is configured to drive an engine fluid pump, such as a fuel pump or oil pump. 4. A method of controlling an aircraft electrical system according to claim 1, wherein the alternating current electrical machine comprises an electrical generator, and the power comprises electrical power provided by the electrical generator. 5. A method of controlling an aircraft electrical system according to claim 1, wherein the fault is sensed on the basis of a measurement of any of current flow or voltage of each phase. 6. A method according to claim 5, wherein the fault is sensed using one or more of overcurrent protection, ground fault protection, unit protection and negative phase sequence protection. 7. A method according to claim 5, wherein the fault is sensed by one or more of a current transformer and a voltage transformer or digital equivalents. 8. A method of controlling an aircraft electrical system according to claim 1, wherein where the power provided by each phase exceeds the power rating of the respective phase, the method comprises overrating the remaining phases until either a normal operation condition or a reversion condition is met. 9. A method according to claim 8, wherein if the normal operation condition is met, the method may comprise restoring the or each non-operational phase of the electrical machine. 10. A method according to claim 8, wherein if the reversion condition is met, the method comprises reducing the power provided by each remaining phase to the rated power, or below the rated power. 11. A method according to any of claim 8, wherein the reversion condition is met where a predetermined period of time has elapsed from the phases exceeding their rated power. 12. A method according to claim 11, wherein the predetermined period of time is calculated on the basis of a measured temperature of the electrical system or a part of the electrical system. 13. A method according to any of claim 8, wherein the reversion condition is met where the electrical system or a part of the electrical system reaches a predetermined temperature. 14. A method according to any of claim 8, wherein the reversion condition is met where required power is less than the rated power of the remaining phases of the electrical machine. 15. A method according to any of claim 8, wherein the normal operation condition is met where each of the phases of the electrical machine is sensed to no longer have a fault. 16. A method according to any of claim 8, wherein the normal condition is met where the respective phase fault detection is found to have been erroneous. 17. A method according to claim 16, wherein the method comprises detecting that the fault occurred on a further electrical component. 18. A method according to claim 17, wherein where the fault is found to be on a further electrical component, the method comprises isolating the further faulty component, and subsequently operating the electrical machine in the normal condition. 19. A method according to claim 3, further comprising sensing relative oil and fuel pressures of fuel and oil systems of the aircraft engine, and operating the respective pumps to maintain a higher oil pressure relative to the fuel pressure. 20. An electrical system for an aircraft, the system comprising: an alternating current electrical machine comprising a plurality of phases, each phase having a power rating, the electrical machine being configured to operate on failure of one or more phases, and a controller, the controller being configured to operate the electrical system in accordance with the method of claim 1.
Rubertus C. Scott ; Weimer Joseph A., Multiple winding channel, magnetic coupling-alterable reluctance electrical machines and their fault tolerant control.
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