Independent power generation in aircraft
First Claim
1. An aircraft, comprising:
- at least one engine;
a plurality of independent power units; and
a fuselage,wherein each power unit of the plurality of independent power units generates electricity independently of the at least one engine during flight, the plurality of independent power units including at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity,wherein the first set of electrical characteristics is different than the second set of electrical characteristics,wherein the second independent power unit provides power to an environmental control system (ECS) configured to provide conditioned air to the fuselage, andwherein, during flight, the ECS is electrically and pneumatically isolated from the at least one engine.
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Accused Products
Abstract
Systems and methods of independent power generation are disclosed. A particular system includes an aircraft having at least one engine and a plurality of independent power units. Each power unit of the plurality of independent power units generates electricity independently of the at least one engine. The plurality of independent power units include at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity. The first set of electrical characteristics is different than the second set of electrical characteristics.
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Citations
20 Claims
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1. An aircraft, comprising:
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at least one engine; a plurality of independent power units; and a fuselage, wherein each power unit of the plurality of independent power units generates electricity independently of the at least one engine during flight, the plurality of independent power units including at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity, wherein the first set of electrical characteristics is different than the second set of electrical characteristics, wherein the second independent power unit provides power to an environmental control system (ECS) configured to provide conditioned air to the fuselage, and wherein, during flight, the ECS is electrically and pneumatically isolated from the at least one engine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. An aircraft, comprising:
a body, comprising; a first independent power unit that provides power to a first set of powered devices; and a second independent power unit that provides power to a second set of powered devices concurrently with the first independent power unit providing power to the first set of powered devices, wherein the first set of powered devices is different than the second set of powered devices, and wherein the second set of power devices includes an environmental control system (ECS) configured to provide conditioned air to a fuselage of the aircraft; and at least one engine coupled to the body, wherein, during flight, neither the first independent power unit nor the second independent power unit receives operational power from the at least one engine, and wherein, during flight, the ECS is electrically and pneumatically isolated from the at least one engine. - View Dependent Claims (18, 19, 20)
Specification