Backup electrical power system for solid-state aircraft power distribution systems
First Claim
1. A backup electrical supply system for an aircraft having a power supply, and an electrically controllable switch adapted to communicate electrical energy from the power supply to one or more electrical loads, comprising:
- a. A user-operable switch having a first terminal in electrical communication with the power supply, and having a second terminal;
b. A first directional current control device having first and second terminals, adapted to permit electrical energy to pass from the first terminal to the second terminal but substantially prevent electrical energy from passing from the second terminal to the first terminal, with the first termination in electrical communication with the second terminal of the user-operable switch;
c. A second directional current control device having first and second terminals, adapted to permit electrical energy to pass from the first terminal to the second terminal but substantially prevent electrical energy from passing from the second terminal to the first terminal, with the first termination in electrical communication with an output of the electrically controllable switch, and the second terminal in electrical communication with the second terminal of the first directional current control device;
d. Wherein second terminals of the first and second directional current control devices can be placed in electrical communication with one or more electrical loads.
4 Assignments
0 Petitions
Accused Products
Abstract
A system comprised of switches, fuses, microprocessor-based monitoring, and a pilot display that provides a method to bypass computer-controlled switching of aircraft power circuits. A backup circuit in addition to the computer-controlled switching circuit provides a method to guarantee power delivery in the case of a failure of the computer-controlled switch. The system provides the pilot with an indication when the backup circuit is engaged. When the other devices are turned off and/or the engine is shut down, an indication can be provided to the pilot that the backup circuit is on. An indication can also be provided to the pilot that the switch is in the off position when it should be on.
33 Citations
22 Claims
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1. A backup electrical supply system for an aircraft having a power supply, and an electrically controllable switch adapted to communicate electrical energy from the power supply to one or more electrical loads, comprising:
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a. A user-operable switch having a first terminal in electrical communication with the power supply, and having a second terminal; b. A first directional current control device having first and second terminals, adapted to permit electrical energy to pass from the first terminal to the second terminal but substantially prevent electrical energy from passing from the second terminal to the first terminal, with the first termination in electrical communication with the second terminal of the user-operable switch; c. A second directional current control device having first and second terminals, adapted to permit electrical energy to pass from the first terminal to the second terminal but substantially prevent electrical energy from passing from the second terminal to the first terminal, with the first termination in electrical communication with an output of the electrically controllable switch, and the second terminal in electrical communication with the second terminal of the first directional current control device; d. Wherein second terminals of the first and second directional current control devices can be placed in electrical communication with one or more electrical loads. - View Dependent Claims (2, 3, 4, 5, 6)
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7. An aircraft electrical control and distribution system, comprising:
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a. An electrical power source; b. A main power bus; c. A first diode; d. A first electrically controllable switch adapted to communicate electrical energy from the main power bus to the input of the first diode; e. A second diode; f. A user-operable switch, adapted to communicate electrical energy from the power supply to the input of the second diode responsive to user actuation of the user-operable switch; g. Wherein the outputs of the first and second diodes are in electrical communication with each other and with one or more first electrical loads. - View Dependent Claims (8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21)
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22. An electrical system for an aircraft having power distribution system, wherein a power supply can be connected to an electrical device using an electrically-controlled switch, comprising:
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a. A failsafe switch to a power supply b. A diode connected between the failsafe switch and the electrical device; c. An electrical sensor adapted to generate a signal representative of electrical power between the failsafe switch and the diode; d. An indication system adapted to communicate the presence, absence, or level of electrical power between the failsafe switch and the diode.
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Specification