Structural element, a battery set, an arrangement of a structural element and a battery set, and an aerospace vehicle

Patent metadata

Field	Value
Publication number	US-11299024-B2
Application number	US-201916422327-A
Country	US
Kind code	B2
Filing date	May 24, 2019
Priority date	Nov 24, 2016
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

An arrangement of a structural element for an aerospace vehicle and a battery set. The structural element extends along a longitudinal direction and has a main web, a first flange and a second flange. The flanges extend away from the main web and are defined by flange edges extending along the longitudinal direction. The first flange, the second flange and the main web form a U-shaped profile defining a cavity. The battery set includes a baseplate and at least one battery on the baseplate. The structural element and the battery set are formed such that the baseplate can be releasably attached to the structural element. The baseplate extends between flange edges and the battery is received in the cavity when the battery set is mounted to the structural element. Further, an aerospace vehicle including such an arrangement, a structural element for an aerospace vehicle and a battery set are disclosed.

First claim

The invention claimed is:

1. An arrangement comprising:
a structural element extending along a longitudinal direction and having a main web, a first flange that extends away from the main web and comprises a first flange edge extending along the longitudinal direction, and a second flange that comprises a second flange edge extending along the longitudinal direction and extends away from the main web in a position spaced apart from the first flange, such that the first flange, the second flange, and the main web form a U-shaped profile defining a cavity; and
a battery set comprising:
a baseplate that is releasably attached to the structural element for mounting the battery set to the structural element, wherein, when the baseplate is attached to the structural element, the baseplate extends from the first flange edge to the second flange edge; and
at least one battery on the baseplate, wherein, when the baseplate is attached to the structural element, the at least one battery on the baseplate is received in the cavity;

wherein an outer surface of the baseplate facing away from the at least one battery on the baseplate is adapted to be part of an outer wall of an aerospace vehicle when mounted to the structural element; and
wherein the structural element is a spar of a wing of the aerospace vehicle and the outer surface of the baseplate is part of a pressure side surface of the wing of the aerospace vehicle.

2. The arrangement of claim 1 , wherein:
the structural element comprises a first stabilizing web portion, which extends the first flange edge in a direction pointing away from the second flange edge and in parallel to the main web, and/or
the structural element comprises a second stabilizing web portion, which extends the second flange edge in a direction pointing away from the first flange edge and in parallel to the main web.

3. The arrangement of claim 1 , wherein the battery set comprises a lock for locking the battery set to the structural element.

4. The arrangement of claim 1 , wherein the structural element comprises a mount for releasably mounting the battery set to the structural element.

5. The arrangement of claim 1 , wherein the structural element comprises a mount for releasably mounting the battery set to the structural element and the battery set comprises a lock for releasably locking the battery set to the structural element.

6. An aerospace vehicle comprising:
a wing with a pressure side surface; and
an arrangement comprising:
a structural element that extends along a longitudinal direction and comprises a main web, a first flange that extends away from the main web and comprises a first flange edge extending along the longitudinal direction, and a second flange that comprises a second flange edge extending along the longitudinal direction and extends away from the main web in a position spaced apart from the first flange, such that the first flange, the second flange, and the main web form a U-shaped profile defining a cavity; and
a battery set comprising:
a baseplate that is releasably attached to the structural element for mounting the battery set to the structural element, wherein, when the baseplate is attached to the structural element, the baseplate extends from the first flange edge to the second flange edge; and
at least one battery on the baseplate, wherein, when the baseplate is attached to the structural element, the at least one battery on the baseplate is received in the cavity;

wherein the structural element is a spar of the wing; and
wherein the pressure side surface of the wing comprises a cutout, such that the battery set can be mounted to structural element.

7. The aerospace vehicle according to claim 6 , wherein an outer surface of the baseplate of the battery set at least partly forms the pressure side surface of the wing in a region of the cutout when the battery set is mounted to the structural element.

8. The aerospace vehicle according to claim 6 , wherein the structural element comprises a mount for releasably mounting the battery set to the structural element.

9. The aerospace vehicle according to claim 8 , wherein the structural element comprises:
a first stabilizing web portion, which extends the first flange edge in a direction pointing away from the second flange edge and in parallel to the main web, and/or
a second stabilizing web portion, which extends the second flange edge in a direction pointing away from the first flange edge and in parallel to the main web.

10. The aerospace vehicle according to claim 6 , wherein the battery set comprises a lock for locking the battery set to the structural element.

11. The aerospace vehicle according to claim 6 , wherein the structural element comprises a mount for releasably mounting the battery set to the structural element and the battery set comprises a lock for releasably locking the battery set to the structural element.

Assignees

• Airbus Operations Gmbh

Inventors

• Linde Peter
• Rostek Peter

Classifications

• H01M50/262

  with fastening means, e.g. locks · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• Y02T10/70

  Energy storage systems for electromobility, e.g. batteries · CPC title