Granted Patent B2

US 12,377,951 · App. 18/214,464 · Granted Aug 5, 2025

Inventor: Mark Allan Page (Long Beach, CA)

Assignee: JETZERO, INC.

B64C1/069B64C39/10B64C2039/105B64C2211/00

Abstract

Claims (42)

1. A system for modular aircraft, the system comprising:

at least a common component, wherein the at least a common component comprises at least a flight component;

a first modular component, wherein the first modular component has a first width and comprises:

a first fuselage component with a first lateral width; and

a first collar component with a second lateral width wider than the first lateral width;

a modular beaver tail disposed at an aft end of the modular aircraft, wherein the modular beaver tail comprises at least a control surface disposed on the modular beaver tail; and

at least an interface component, wherein the at least an interface component comprises:

a first end configured to connect to the at least a common component;

a second end configured to connect to the at least a first modular component, wherein connection of the at least a common component, the first modular component and the at least an interface component forms a blended wing body having:

a first wingspan that is a function of the first lateral width; and

a smooth transition along a leading edge of the blended wing body with no clear dividing line; and

a latching mechanism comprising an electronically actuated mechanism, wherein the electronically actuated mechanism is configured to removably connect the at least a common component and the modular beaver tail.

2. The system of claim 1 , wherein the first collar component comprises one or more openings configured to be passenger doors.

3. The system of claim 1 , wherein the first collar component comprises one or more openings configured to be cargo doors.

4. The system of claim 1 , wherein the first collar component is configured to provide a smooth transition between a nose portion and the at least a common component.

5. The system of claim 1 , wherein the connection of the at least a common component, the first modular component, and the at least an interface component further forms the blended wing body having a smooth transition between the at least a common component and the collar component.

6. The system of claim 1 , wherein the first modular component further comprises carbon fiber.

7. The system of claim 1 , wherein the at least a common component further comprises at least a portion of a wing.

8. The system of claim 1 , wherein the first modular component is configured to provide a continuous outer mold line.

9. The system of claim 1 , wherein the first modular component further comprises a main body of the modular aircraft.

10. A method of manufacturing a modular aircraft, the method comprising:

receiving at least a common component, wherein the at least a common component comprises at least a flight component;

receiving a first modular component, wherein the first modular component has a first width and comprises:

a first fuselage component with a first lateral width; and

a first collar component with a second lateral width wider than the first lateral width;

receiving a modular beaver tail disposed at an aft end of the modular aircraft, wherein the modular beaver tail comprises at least a control surface disposed on the modular beaver tail;

receiving at least an interface component, wherein the at least an interface component comprises:

a first end and a second end; and

a latching mechanism comprising an electronically actuated mechanism;

connecting, removably, using the electronically actuated mechanism, the at least a common component and the modular beaver tail;

connecting the at least a common component at the first end of the interface component; and

connecting the at least a first modular component to the second end, wherein connection of the at least a common component, the first modular component and the at least an interface component forms a blended wing body having:

a first wingspan that is a function of the first lateral width; and

a smooth transition along a leading edge of the blended wing body with no clear dividing line.

11. The method of claim 10 , wherein the first collar component comprises one or more openings configured to be passenger doors.

12. The method of claim 10 , wherein the first collar component comprises one or more openings configured to be cargo doors.

13. The method of claim 10 , further comprising, providing, by the first collar component, a smooth transition between a nose portion and the at least a common component.

14. The method of claim 10 , wherein the connection of the at least a common component, the first modular component, and the at least an interface component further forms the blended wing body having a smooth transition between the at least a common component and the collar component.

15. The method of claim 10 , wherein the first modular component further comprises carbon fiber.

16. The method of claim 10 , wherein the at least a common component further comprises at least a portion of a wing.

17. The method of claim 10 , further comprising, providing, by the first modular component, a continuous outer mold line of the modular aircraft.

18. The method of claim 10 , wherein the first modular component further comprises a main body of the modular aircraft.

Assignments (1)

Continuity (2)

References Cited (42)