Granted Patent B2

US 12,559,220 · App. 18/101,877 · Granted Feb 24, 2026

Inventor: Blaine Rawdon (Long Beach, CA)

Assignee: JetZero, Inc.

B64C1/061B64C1/10B64C1/12B64C39/10B64C2039/105

Abstract

Claims (45)

1 . An airframe of a blended wing body aircraft, the airframe comprising:

a multi-chamber airframe comprising:

carbon fiber-based composite; and

at least two non-cylindrical cabin chambers attached together;

a plurality of longitudinal stiffeners running substantially parallel to a longitudinal axis of the airframe and directly connected to a top side of the airframe and through a planar base of the airframe, wherein the plurality of longitudinal stiffeners are configured to compartmentalize the airframe into the at least two non-cylindrical cabin chambers;

at least a laterally outermost bulkhead configured to resist a cabin pressure;

a skin comprising an outer mold line of the airframe and configured to attach to the plurality of longitudinal stiffeners at the top side of the airframe and a bottom side of the airframe;

at least an aft pressure bulkhead running substantially orthogonal to the longitudinal axis, extending from the top side of the airframe to the bottom side of the airframe configured to resist the cabin pressure, wherein the aft pressure bulkhead is a rear pressure containing component configured to resist pressure loading between an atmosphere and a cabin at an aft of the aircraft; and

a plurality of support elements situated orthogonal to the plurality of longitudinal stiffeners, wherein a support element of the plurality of support elements comprises at least one arc-shaped support element attached to at least one longitudinal stiffener.

2 . The airframe of claim 1 , wherein the support element is configured to be attached to adjacent longitudinal stiffeners of the plurality of longitudinal stiffeners.

3 . The airframe of claim 1 , wherein the skin comprises an upper skin at the top side of the airframe and a lower skin at the bottom side of the airframe.

4 . The airframe of claim 1 , further comprising at least an additional support element comprising:

a straight stiffener attached to an adjacent pair of longitudinal stiffeners of the plurality of longitudinal stiffeners,

wherein the at least one arc-shaped support element is positioned below the straight stiffener.

5 . The airframe of claim 1 , wherein the planar base extends over the longitudinal axis and a lateral axis of the airframe.

6 . The airframe of claim 5 , wherein:

the planar base comprises a plurality of lateral beams; and

the plurality of longitudinal stiffeners is each attached to one or more of the plurality of lateral beams of the planar base.

7 . The airframe of claim 1 , further comprising at least an additional support element comprising:

a stiffener attached to an adjacent pair of longitudinal stiffeners of the plurality of longitudinal stiffeners; and

a plurality of tensioners, each tensioner of the plurality of tensioners having a first end and a second end;

wherein the first end is attached to the stiffener and the second end is attached to one longitudinal stiffener of the adjacent pair of longitudinal stiffeners.

8 . The airframe of claim 7 , wherein the second end of each tensioner of the plurality of tensioners is attached to each longitudinal stiffener at a same location.

9 . A method of manufacturing an airframe of a blended wing body aircraft, the method comprising:

installing a multi-chamber airframe comprising:

carbon-fiber based composite; and

at least two non-cylindrical cabin chambers attached together;

installing a plurality of longitudinal stiffeners substantially parallel to a longitudinal axis of the airframe, directly connected to a top side of the airframe and through a planar base, wherein the plurality of longitudinal stiffeners are configured to compartmentalize the airframe into the at least two non-cylindrical cabin chambers and wherein the plurality of longitudinal stiffeners comprise:

at least a laterally outermost bulkhead configured to resist a cabin pressure;

attaching a skin, comprising an outer mold line of the airframe, to the plurality of longitudinal stiffeners at the top side of the airframe and a bottom side of the airframe;

installing at least an aft pressure bulkhead substantially orthogonal to the longitudinal axis, extending from the top side of the airframe to the bottom side of the airframe configured to resist the cabin pressure wherein the aft pressure bulkhead is a rear pressure containing component; and

installing a plurality of support elements situated orthogonal to the plurality of longitudinal stiffeners, wherein a support element of the plurality of support elements comprises at least one arc-shaped support element attached to at least one longitudinal stiffener.

10 . The method of claim 9 , wherein the support element is attached to adjacent longitudinal stiffeners of the plurality of longitudinal stiffeners.

11 . The method of claim 9 , wherein the skin comprises an upper skin at the top side of the airframe and a lower skin at the bottom side of the airframe.

12 . The method of claim 9 , further comprising installing at least an additional support element, wherein installing the at least an additional support element further comprises:

attaching a straight stiffener to an adjacent pair of longitudinal stiffeners of the plurality of longitudinal stiffeners;

and

positioning the at least one arc-shaped support element below the straight stiffener.

13 . The method of claim 9 , wherein the planar base extends over the longitudinal axis and a lateral axis of the airframe.

14 . The method of claim 13 , wherein the planar base comprises a plurality of lateral beams, and wherein the method further comprises attaching each of the plurality of longitudinal stiffeners to one or more of the plurality of lateral beams of the planar base.

15 . The method of claim 9 , further comprising installing at least an additional support element, wherein installing the at least an additional support element comprises:

attaching a stiffener to an adjacent pair of longitudinal stiffeners of the plurality of longitudinal stiffeners;

installing a plurality of tensioners, each tensioner of the plurality of tensioners having a first end and a second end; and

attaching the first end to the stiffener and the second end to one longitudinal stiffener of the adjacent pair of longitudinal stiffeners.

16 . The method of claim 15 , further comprising attaching the second end of each tensioner of the plurality of tensioners to each longitudinal stiffener at a same location.

Assignments (1)

Continuity (1)

References Cited (31)