IP Library › Patent Application 19651012
Patent Application
App. No. 19/651,012

HIGH POWER DISTRIBUTION ARCHITECTURES

Loading inventors, assignments & file history…
Monitor This Case
Get email alerts when status or documents change.
Order Certified Copies
Most orders are placed with the USPTO same day — all within 24 business hours.
Order via The Patent Place →
Pre-filled with this patent's details
Quick Facts
Patent No.
US None
App. No.
19/651,012
Abstract

A power distribution system for an aircraft, comprising a plurality of electric propeller units (EPUs), a first paired battery pack unit, and a second paired battery pack unit. The first paired battery pack unit may include a first battery pack electrically connected to a second battery pack via a first battery pack cross-link. The first battery pack may be configured to provide power to a first set of EPUs, and the second battery pack is configured to provide power to a second set of EPUs. The second paired battery pack unit may include a third battery pack electrically connected to a fourth battery pack via a second battery pack cross-link. The third battery pack may be configured to provide power to a third set of EPUs, and the fourth battery pack may be configured to provide power to a fourth set of EPUs.

Claims (51)

1 - 95 . (canceled)

96 . A power distribution system for an aircraft, comprising:

a plurality of electric propeller units (EPUs);

a first paired battery pack unit, the first paired battery pack unit comprising a first battery pack electrically connected to a second battery pack via a first battery pack cross-link, wherein the first battery pack is configured to provide power to a first set of EPUs of the plurality of EPUs, wherein the second battery pack is configured to provide power to a second set of EPUs of the plurality of EPUs; and

a second paired battery pack unit, the second paired battery pack unit comprising a third battery pack electrically connected to a fourth battery pack via a second battery pack cross-link, wherein the third battery pack is configured to provide power to a third set of EPUs of the plurality of EPUs, wherein the fourth battery pack is configured to provide power to a fourth set of EPUs of the plurality of EPUs.

97 . The system of claim 96 , wherein the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs.

98 . The system of claim 96 , wherein the first battery pack cross-link and the second battery pack cross-link are electrically separate from one another.

99 . The system of claim 96 , wherein:

the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs;

the second battery pack is configured to provide backup power across the first battery pack cross-link to the first set of EPUs;

the third battery pack is configured to provide backup power across the second battery pack cross-link to the fourth set of EPUs; and

the fourth battery pack is configured to provide backup power across the second battery pack cross-link to the third set of EPUs.

100 . The system of claim 96 , wherein:

the first battery pack cross-link comprises a first pyro-technical fuse; and

the first set of EPUs is electrically separated from the second set of EPUs upon activation of the first pyro-technical fuse.

101 . The system of claim 100 , wherein:

the second battery pack cross-link comprises a second pyro-technical fuse; and

the third set of EPUs is electrically separated from the fourth set of EPUs upon activation of the second pyro-technical fuse.

102 . The system of claim 96 , wherein the first paired battery pack unit the second paired battery pack unit are electrically separate from one another.

103 . The system of claim 96 , wherein each EPU of the plurality of EPUs comprises an associated fuse, wherein, upon activation of the fuse, the associated EPU is disconnected from an associated battery pack.

104 . The system of claim 96 , wherein each battery pack comprises an associated charging contactor, wherein, upon opening the charging contactor, the associated battery pack is disconnected from a high voltage charging bus.

105 . The system of claim 96 , wherein each of the sets of EPUs comprises two EPUs.

106 . The system of claim 96 , wherein each of the sets of EPUs comprises two diagonally symmetric EPUs.

107 . The system of claim 106 , wherein:

the first paired battery pack unit is configured to provide power to a front outboard EPU, a front inboard EPU, a rear outboard EPU, and a rear inboard EPU.

108 . The system of claim 96 , wherein the first battery pack is configured to independently power the first set of EPUs and the second battery pack is configured to independently power the second set of EPUs.

109 . An aircraft, comprising:

a plurality of electric propeller units (EPUs);

a battery management system;

a first paired battery pack unit, the first paired battery pack unit comprising a first battery pack electrically connected to a second battery pack via a first battery pack cross-link, wherein the first battery pack is configured to provide power to a first set of EPUs of the plurality of EPUs, wherein the second battery pack is configured to provide power to a second set of EPUs of the plurality of EPUs; and

a second paired battery pack unit, the second paired battery pack unit comprising a third battery pack electrically connected to a fourth battery pack via a second battery pack cross-link, wherein the third battery pack is configured to provide power to a third set of EPUs of the plurality of EPUs, wherein the fourth battery pack is configured to provide power to a fourth set of EPUs of the plurality of EPUs.

110 . The aircraft of claim 109 , wherein the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs after the first battery pack is disconnected from the second battery pack by the battery management system.

111 . The aircraft of claim 109 , wherein the first battery pack cross-link and the second battery pack cross-link are electrically separate from one another.

112 . The aircraft of claim 109 , wherein:

the first battery pack is configured to provide backup power across the first battery pack cross-link to the second set of EPUs;

the second battery pack is configured to provide backup power across the first battery pack cross-link to the first set of EPUs;

the third battery pack is configured to provide backup power across the second battery pack cross-link to the fourth set of EPUs; and

the fourth battery pack is configured to provide backup power across the second battery pack cross-link to the third set of EPUs.

113 . The aircraft of claim 109 , wherein:

the first battery pack cross-link comprises a first pyro-technical fuse; and

the first set of EPUs is electrically separated from the second set of EPUs upon activation of the first pyro-technical fuse.

114 . the aircraft of claim 113 , wherein:

the second battery pack cross-link comprises a second pyro-technical fuse; and

the third set of EPUs is electrically separated from the fourth set of EPUs upon activation of the second pyro-technical fuse.

115 . The aircraft of claim 109 , wherein the first paired battery pack unit and the second paired battery pack unit are electrically separate from one another.

116 . The aircraft of claim 109 , wherein each EPU of the plurality of EPUs comprises an associated fuse, wherein, upon activation of the fuse, the associated EPU is disconnected from an associated battery pack.

117 . The aircraft of claim 109 , wherein each battery pack comprises an associated charging contactor, wherein, upon opening the charging contactor, the associated battery pack is disconnected from a high voltage charging bus.

118 . The aircraft of claim 109 , wherein each of the sets of EPUs comprises two EPUs.

119 . The aircraft of claim 109 , wherein each of the sets of EPUs comprises two diagonally symmetric EPUs.

120 . The aircraft of claim 119 , the first paired battery pack unit is configured to provide power to a front outboard EPU, a front inboard EPU, a rear outboard EPU, and a rear inboard EPU.

121 . The aircraft of claim 109 , wherein the first battery pack is configured to independently power the first set of EPUs and the second battery pack is configured to independently power the second set of EPUs.