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Systems and methods for controlling aricraft electrical power

A power system and aircraft technology, applied in the direction of auxiliary power equipment, fluid pressure actuation system components, power distribution, etc., can solve problems such as passenger boredom

Active Publication Date: 2008-03-12
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] One disadvantage of the foregoing approach is that the electrically driven pump tends to cycle repeatedly between high and low output settings as the demand for hydraulic fluid pressure fluctuates
Because the hydraulic pump can be placed directly under the cabin, the roaring noise can be audible and annoying to passengers

Method used

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  • Systems and methods for controlling aricraft electrical power
  • Systems and methods for controlling aricraft electrical power
  • Systems and methods for controlling aricraft electrical power

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Embodiment Construction

[0015] The present disclosure describes systems and methods for controlling aircraft electrical power. Certain specific details are set forth in the following description and FIGS. 1-5 to provide a thorough understanding of various embodiments of the invention. Well-known structures, systems and methods that are often associated with such systems have not been shown or described in detail to avoid unnecessarily obscuring the description of the various embodiments of the invention. Additionally, those of ordinary skill in the art will understand that other embodiments of the invention may be practiced without several of the details described below.

[0016] Several embodiments of the invention described below can take the form of computer-executable instructions, including routines, executed by programmable computers. Those skilled in the art will appreciate that the invention can be practiced on other computer or analog systems than those shown and described below. The inven...

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PUM

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Abstract

Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

Description

technical field [0001] The present disclosure is generally directed to systems and methods for controlling electrical power in an aircraft, including controlling the operation of motor controllers in a manner dependent on the mode of operation of the aircraft, and / or substituting one motor controller for another One. Background technique [0002] Aircraft manufacturers are under continuous pressure to reduce the power required by commercial transport aircraft and to increase the efficiency with which such aircraft are used to operate. One way to accomplish these goals is to replace equipment that has historically been powered by bleed air or shaft output from aircraft engines with electrically powered equipment. For example, hydraulic pumps on newer generation aircraft are now driven by electric motors. Hydraulic pumps pressurize hydraulic fluid, which in turn is used to power many aircraft systems, including landing gear, high lift devices (e.g., leading edge equipment a...

Claims

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Application Information

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IPC IPC(8): F15B21/08
CPCH02J4/00B64D41/00B64D2221/00H02J2310/44
Inventor 杰弗里·J·怀特戴维·K·托伊J·E·格罗特
Owner THE BOEING CO
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