Blended wing body aircraft with transmissive panels
The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transmissive panels integrated into a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.
1 . A blended wing body (BWB) aircraft with transparent structural panels, wherein the blended wing body aircraft comprises:
a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the blended wing body aircraft;
a cabin located within one or more of the main body and a transitional portion of the blended wing body;
an internal structure of the blended wing body, wherein the internal structure comprises at least two ribs and a plurality of frames, wherein a frame of a plurality of frames comprises a space in between the at least two ribs, wherein the plurality of frames comprises a first plurality of frames and a second plurality of frames; and
a plurality of transmissive panels, wherein each transmissive panel of the plurality of transmissive panels is located within a frame of the first plurality of frames, wherein each frame of the second plurality of frames do not contain transmissive panels, wherein the plurality of transmissive panels comprises a first plurality of transmissive panels and a second plurality of transmissive panels integrated within a surface of the blended wing body, wherein the at least two ribs and a channel are located between the first plurality of transmissive panels and the second plurality of transmissive panels, and wherein the transmissive panels comprise a transmissive composite, including translucent fiberglass that is configured to transmit and scatter visible light and a rough surface finish configured to increase the scatter of visible light.
2 . The aircraft of claim 1 , wherein the aircraft further includes a skin compatible with transmissive panels.
3 . The aircraft of claim 2 , wherein the skin is comprised of an opaque composite.
4 . The aircraft of claim 3 , wherein the opaque composite is thinner than the transmissive composite.
5 . The aircraft of claim 1 , further comprising a skin which makes up at least a portion of an outer mold line of the blended wing body, wherein the skin comprises an opaque composite, including carbon fiber; and
wherein the carbon fiber opaque composite skin and translucent fiberglass transmissive composite transmissive panels are formed together during a molding process.
6 . The aircraft of claim 5 , wherein the cabin comprises a plurality of sections separated by the at least two ribs; and at least a transmissive panel of the plurality of transmissive panels spans at least a section of the plurality of sections.
7 . The aircraft of claim 1 , wherein the plurality of transmissive panels is configured to transmit natural light from outside the blended wing body aircraft to inside the blended wing body aircraft.
8 . The aircraft of claim 1 , wherein the plurality of transmissive panels are located on an upper surface of the blended wing body aircraft.
9 . The aircraft of claim 1 , wherein the plurality of transmissive panels form three rows which extend laterally fore to aft.
10 . A method of manufacture for a blended wing body (BWB) aircraft with transparent structural panels, the method comprising:
receiving a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the blended wing body aircraft;
locating a cabin within one or more of the main body and a transitional portion of the blended wing body;
locating an internal structure of the blended wing body, wherein the internal structure comprises at least two ribs and a plurality of frames, wherein a frame of the plurality of frames comprises a space in between the at least two ribs, wherein the plurality of frames comprises a first plurality of frames and a second plurality of frames; and
locating a plurality of transmissive panels, wherein each transmissive panel of the plurality of transmissive panels is located within a frame of the first plurality of frames, wherein each frame of the second plurality of frames do not contain transmissive panels, wherein the plurality of transmissive panels comprises a first plurality of transmissive panels and a second plurality of transmissive panels integrated within a surface of the blended wing body, wherein the at least two ribs and a channel are located between the first plurality of transmissive panels and the second plurality of transmissive panels, and wherein the plurality of transmissive panels comprise a transmissive composite, including translucent fiberglass that is configured to transmit and scatter visible light and a rough surface finish configured to increase the scatter of visible light.
11 . The method of claim 10 , wherein the aircraft further includes a skin compatible with transmissive panels.
12 . The method of claim 11 , wherein the skin is comprised of an opaque composite.
13 . The method of claim 12 , wherein the opaque composite is thinner than the transmissive composite.
14 . The method of claim 10 , wherein the aircraft further comprises a skin which makes up at least a portion of an outer mold line of the blended wing body, wherein the skin comprises an opaque composite, including carbon fiber and the method further comprises:
forming the carbon fiber opaque composite skin and translucent fiberglass transmissive composite transmissive panels together during a molding process.
15 . The method of claim 14 , wherein the cabin comprises a plurality of sections separated by the at least two ribs; and at least a transmissive panel of the plurality of transmissive panels spans at least a section of the plurality of sections.
16 . The method of claim 10 , further comprising configuring the plurality of transmissive panels to transmit natural light from outside the blended wing body aircraft to inside the blended wing body aircraft.
17 . The method of claim 10 , wherein the plurality of transmissive panels comprises a turbid material.
18 . The method of claim 10 , further comprising locating the plurality of transmissive panels on an upper surface of the blended wing body.
19 . The method of claim 10 , wherein the plurality of transmissive panels form three rows which extend laterally fore to aft.