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Active voltage control for hybrid electric aircraft

A voltage controller and aircraft technology, applied in aircraft, battery/fuel cell control devices, engine-driven traction, etc., to achieve the effects of prolonging battery life, saving costs, and reliable architecture

Pending Publication Date: 2020-09-08
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] There is no solution for active power flow control and battery fuel management control for hybrid electric aircraft with batteries with hundreds of kWh of energy

Method used

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  • Active voltage control for hybrid electric aircraft
  • Active voltage control for hybrid electric aircraft
  • Active voltage control for hybrid electric aircraft

Examples

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Embodiment Construction

[0026] Exemplary embodiments of systems and methods for actively controlling the voltage of a bus supplying power from a battery and / or generator to a propulsion motor of a hybrid electric aircraft are described in detail below. However, not all features of an actual implementation are described in this specification. Those skilled in the art will appreciate that in the development of any such implementation, a number of implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related constraints and business-related constraints, This will vary by implementation. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking for those of ordinary skill in the art having the benefit of this disclosure.

[0027] A single hybrid electric aircraft may have one or more sources of HVDC electrical power (eg, batteries) and one or mor...

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Abstract

The invention provides an active voltage control for hybrid electric aircraft, and relates to a solid-state high-voltage direct-current (HVDC) bus voltage controller to provide active power flow control in a hybrid electric aircraft power supply system. The HVDC bus voltage controller includes an active voltage controller and an active rectifier unit configured to control the HVDC bus voltage using the PWM control technique. In one implementation, the active rectifier unit includes high-power and high-frequency semiconductor switches with fast turn-off capabilities. The active voltage controller sends an HVDC bus reference voltage to the active rectifier unit. The low-level controller inside the active rectifier unit is configured to control the HVDC bus voltage to match the HVDC bus reference voltage.

Description

technical field [0001] The present disclosure generally relates to hybrid electrical power sources having two or more electrical energy sources that provide energy to a connected load. In particular, the technology disclosed herein relates to hybrid electric power sources that include one or more batteries and one or more generators driven by an internal combustion or gas turbine engine. Background technique [0002] Some aircraft have electric propulsion systems (hereinafter referred to as "electric aircraft"). In such aircraft, electric motors convert electrical power into mechanical power for use by the propulsion system. For example, an electric motor may turn one or more propellers on the aircraft to provide thrust. Electric flying vehicles can take various forms. For example, an electric aircraft may be an aircraft, rotorcraft, helicopter, quadrotor, unmanned aerial vehicle, or some other suitable type of aircraft. [0003] When electric motors are used for propuls...

Claims

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Application Information

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IPC IPC(8): H02J7/34B60L58/10B60L58/12
CPCH02J7/34H02J7/007B60L58/10B60L58/12B60L2200/10B60L2240/44B60L2240/547B60L2240/549H02J7/1415H02J7/1492H02J2310/44Y02T10/72Y02T10/70B60L50/13B60R16/033B60L58/20B60L15/2045
Inventor E·V·索洛多夫尼克M·E·利夫苓K·J·卡里米
Owner THE BOEING CO
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