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An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air c

An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).

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What is claimed is: 1. An electrical architecture for an aircraft having an engine, the electrical architecture comprising: an electrical generator component coupled to the engine, the electrical generator component being configured to receive mechanical power from the engine and to generate a cons

What is claimed is: 1. An electrical architecture for an aircraft having an engine, the electrical architecture comprising: an electrical generator component coupled to the engine, the electrical generator component being configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the mechanical power; and an air compression system comprising a compressor motor subsystem that lacks a motor controller, the air compression system coupled to the electrical generator component and configured to receive the constant frequency AC electrical power as an input and, in response thereto, produce a pressurized air output having variable characteristics. 2. The electrical architecture of claim 1, the air compression system being configured to produce a pressurized air output having a variable air flow rate. 3. The electrical architecture of claim 1, the air compression system being configured to produce a pressurized air output having a variable air pressure. 4. The electrical architecture of claim 1, the air compression system comprising a compressor motor subsystem that lacks power electronics components. 5. The electrical architecture of claim 1, wherein: the engine is a jet engine; the electrical generator component is configured to receive shaft power from the jet engine; and the electrical generator component is configured to generate the constant frequency AC electrical power from the shaft power. 6. The electrical architecture of claim 1, the air compression system comprising a multi-step compressor architecture. 7. The electrical architecture of claim 1, the air compression system comprising a staged compressor architecture. 8. The electrical architecture of claim 1, the air compression system comprising a variable geometry compressor architecture. 9. The electrical architecture of claim 1, the air compression system comprising an open differential compressor architecture. 10. The electrical architecture of claim 1, the air compression system comprising a multiple motor architecture. 11. The electrical architecture of claim 1, the air compression system comprising a multi-speed motor architecture. 12. An electrical architecture for an aircraft having an engine, the electrical architecture comprising: an electrical generator component coupled to the engine, the electrical generator component being configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the mechanical power; and an air compression system comprising a compressor motor subsystem that lacks power electronics components, the air compression system coupled to the electrical generator component and configured to receive the constant frequency AC electrical power as an input and, in response thereto, produce a pressurized air output having variable characteristics. 13. An electrical architecture for an aircraft having an engine, the electrical architecture comprising: an electrical generator component coupled to the engine, the electrical generator component being configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the mechanical power; and an air compression system comprising one of a multi-step compressor architecture, a staged compressor architecture, a variable geometry compressor architecture, an open differential compressor architecture, a multiple motor architecture and a multi-speed motor architecture, the air compression system coupled to the electrical generator component and configured to receive the constant frequency AC electrical power as an input and, in response thereto, produce a pressurized air output having variable characteristics.