초록 ▼

Regenerated power from actuation loads of an aircraft may be returned to the distribution bus of the aircraft. In the past, actuators were either hydrostatic or pneumatic. With the furtherance of more electric architecture (MEA) aircraft, there has been an increase in electrical actuation modes. The

Regenerated power from actuation loads of an aircraft may be returned to the distribution bus of the aircraft. In the past, actuators were either hydrostatic or pneumatic. With the furtherance of more electric architecture (MEA) aircraft, there has been an increase in electrical actuation modes. The power or current exchange between electrical buses and the electromechanical and electro-hydrostatic flight control actuators is bidirectional, resulting in a need to accommodate regenerative power. Conventional methods may use shunt regulation to dissipate regenerated power. These methods require additional cooling to reject the heat generated. This regenerated power is wasted as dissipated heat. The present invention, on the other hand, may dump the regenerated power back to a power sink, such as into ancillary electrical loads or to the starter/generator as mechanical (kinetic) energy. In the present invention, the energy may not be wasted nor may it generate excessive heat that needs to be dissipated.

대표청구항 ▼

1. A power system for an aircraft comprising: electromechanical control surface actuators adapted to either consume electrical power during operation or regenerate electrical power during operation;a prime mover providing power to mechanical power loads;an electrical machine that either converts mec

1. A power system for an aircraft comprising: electromechanical control surface actuators adapted to either consume electrical power during operation or regenerate electrical power during operation;a prime mover providing power to mechanical power loads;an electrical machine that either converts mechanical energy from the prime mover to electrical energy or converts electrical energy to supply mechanical energy to the prime mover; anda bidirectional inverter converter controller (ICC) that converts power between the electrical machine and a power bus and controls power flow between the power bus and the electric machine,wherein the power bus is a bidirectional bus that delivers power between the ICC and the control surface actuators and between the ICC and ancillary electrical loads of the aircraft,wherein the ICC transmits electrical power from the electrical machine to the bus when power consumption of the control surface actuators and the ancillary loads is positive,wherein the ICC transmits electrical power to the ancillary electrical loads when the control surface actuators regenerate electrical power, andwherein the ICC transmits portions of the electrical power regenerated by the control surface actuators to the electrical machine when the regenerated power exceeds power consumption of the ancillary loads. 2. The power system of claim 1, wherein the power bus is a DC bus. 3. The power system of claim 1, further comprising a dynamic brake for slowing the prime mover when the power regenerated by the actuation loads exceeds the power needed for the ancillary loads. 4. The power system of claim 1, wherein the power system is integrated into an electrical load regeneration management system of an aircraft. 5. An electrical load regeneration management system for an aircraft comprising: a bidirectional power bus that delivers electrical power to a plurality of control surface actuators and that receives regenerated power from the control surface actuators;a power sink that receives and consumes the regenerated power as it is being produced without any intermediate transmission to an energy storage device, the power sink including ancillary electrical loads, wherein the ancillary electrical loads draw a constant current; anda bidirectional inverter, converter controller (ICC) that transmits portions of the regenerated power that exceed the ancillary electrical loads to an electric machine the converts the excess regenerated power to mechanical energy in an engine of the aircraft. 6. A method for managing electrical load regeneration in an aircraft, the method comprising: providing electrical power to a power bus, the power bus electrically connected to ancillary loads and control surface actuators, which actuators are capable of consuming or regenerating electrical power during operation;receiving power regenerated by the actuators into the power bus; anddelivering the regenerated power to at least one of the ancillary loads as electrical energy and, when the regenerated power is in excess of that needed for the ancillary loads, converting the regenerated power into mechanical energy by driving an electric machine connected to a prime mover of the aircraft. 7. The method of claim 6, further comprising slowing the prime mover with a dynamic brake when the regenerated power exceeds the power required for the ancillary loads. 8. The method of claim 6, wherein the regenerated power is consumed as it is being produced without any intermediate transmission to an energy storage device.