- Document Number:
20240300636
- Appl. No:
18/118808
- Application Filed:
March 08, 2023
- نبذة مختصرة :
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.
- Assignees:
JETZERO, INC. (Long Beach, CA, US)
- Claim:
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; and a plurality of transmissive panels integrated within a surface of the blended wing body, wherein the transmissive panels comprise a transmissive composite, including translucent fiberglass that is configured to transmit and scatter visible light.
- Claim:
2. 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.
- Claim:
3. (canceled)
- Claim:
4. (canceled)
- Claim:
5. (canceled)
- Claim:
6. The aircraft of claim 1, wherein the aircraft further includes a skin compatible with transmissive panels.
- Claim:
7. The aircraft of claim 6, wherein the skin is comprised of an opaque composite.
- Claim:
8. The aircraft of claim 7, wherein the opaque composite is thinner than the transmissive composite.
- Claim:
9. The aircraft of claim 1, wherein the plurality of transmissive panels are located on an upper surface of the blended wing body aircraft.
- Claim:
10. (canceled)
- Claim:
11. 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; and locating a plurality of transmissive panels integrated within a surface of the blended wing body, wherein the plurality transmissive panels comprise a transmissive composite, including translucent fiberglass that is configured to transmit and scatter visible light.
- Claim:
12. The method of claim 11, 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.
- Claim:
13. The method of claim 11, wherein the plurality of transmissive panels comprises a turbid material.
- Claim:
14. (canceled)
- Claim:
15. (canceled)
- Claim:
16. The method of claim 11, wherein the aircraft further includes a skin compatible with transmissive panels.
- Claim:
17. The method of claim 16, wherein the skin is comprised of an opaque composite.
- Claim:
18. The method of claim 17, wherein the opaque composite is thinner than the transmissive composite.
- Claim:
19. The method of claim 11, further comprising locating the plurality of transmissive panels on an upper surface of the blended wing body.
- Claim:
20. (canceled)
- Claim:
21. The aircraft of claim 1, wherein the plurality of transmissive panels form three rows which extend laterally fore to aft.
- Claim:
22. 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 the translucent fiberglass transmissive composite transmissive panels are formed together during a molding process.
- Claim:
23. The aircraft of claim 22, wherein the cabin comprises a plurality of sections separated by ribs; and at least a transmissive panel of the plurality of transmissive panels spans at least a section of the plurality of sections.
- Claim:
24. The method of claim 11, wherein the plurality of transmissive panels form three rows which extend laterally fore to aft.
- Claim:
25. The method of claim 11, 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 the translucent fiberglass transmissive composite transmissive panels together during a molding process.
- Claim:
26. The aircraft of claim 22, wherein the cabin comprises a plurality of sections separated by ribs; and at least a transmissive panel of the plurality of transmissive panels spans at least a section of the plurality of sections.
- Current International Class:
64; 64; 64
- الرقم المعرف:
edspap.20240300636
Processing Request
No Comments.