US 12,240,625 B2
DC bus voltage control
Richard Freer, Saint-Basile-le-Grand (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Feb. 16, 2023, as Appl. No. 18/110,565.
Application 18/110,565 is a continuation of application No. 17/402,474, filed on Aug. 13, 2021, granted, now 11,649,065.
Prior Publication US 2024/0283360 A1, Aug. 22, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. H02M 3/158 (2006.01); B64D 27/24 (2006.01); B64D 41/00 (2006.01); H02J 1/00 (2006.01); H02M 1/00 (2007.01); H02M 1/32 (2007.01)
CPC B64D 41/00 (2013.01) [B64D 27/24 (2013.01); H02J 1/00 (2013.01); H02M 1/0022 (2021.05); H02M 1/007 (2021.05); H02M 1/327 (2021.05); H02M 3/158 (2013.01); B64D 2221/00 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A system for controlling aircraft power in an aircraft, the system comprising:
a DC/DC electrical power converter configured to be connected to an aircraft system via a conductor having a dielectric insulation disposed therearound, the dielectric insulation rated for an altitude less than a maximum service altitude of the aircraft, the converter including:
a DC input and a DC output; and
a switching circuit connecting the DC input to the DC output and operable to vary a voltage at the DC output; and
a control module operatively connected to the switching circuit for variable control of the voltage at the DC output, the control module being operative to:
receive input indicative of an altitude of the aircraft; and
cause the switching circuit to set the voltage of the DC output to at most a maximum voltage value, the maximum voltage value determined as a function of the altitude of the aircraft and corresponding to a voltage value above which a risk of electrical arcing via the conductor and through the dielectric insulation is increased for the altitude.