Granted Patent B2

US 12,654,853 · App. 18/026,756 · Granted Jun 16, 2026

Inventors: Andrew Dudley Moore (Stanmore, AU); Alfred Leonard Swallow (Stanmore, AU)

Assignee: AMSL INNOVATIONS PTY LTD

B64C39/08B64C1/26B64C5/06B64C29/0033B64C39/068B64D27/31B64D27/34B64C3/14

Abstract

Claims (18)

1 . An aircraft structure comprising:

a fuselage;

first and second forward wings mounted to and/or extending from opposing sides of the fuselage;

a continuous rear wing span defining first and second rear wings and a central static connecting portion;

a first wing connecting member extending between the first forward wing and the first rear wing;

a second wing connecting member extending between the second forward wing and the second rear wing; and

first and second electric motors each having rotors, are mounted to each wing, each rotor is pivotal between a first configuration for vertical flight, and a second configuration for forward flight,

wherein the rear wing span is supported by a centrally located V tail joint defined by first and second angularly inclined arms, and

wherein the first and second angularly inclined arms are joined at a proximal lower end, and wherein the proximal lower end is mounted between a rear bulkhead of the fuselage and a tail cone such that the proximal lower end is internally housed in an internal cavity formed by the rear bulkhead and the tail cone.

2 . The aircraft structure of claim 1 , wherein each arm has a distal exposed portion which extends above the tail cone.

3 . The aircraft structure of claim 2 , wherein the distal exposed portion has an aerodynamic fairing on a leading edge.

4 . The aircraft structure of claim 3 , wherein an aerodynamic shield is located at a junction where the distal exposed portion of each arm extends upwardly beyond the fuselage.

5 . The aircraft structure of claim 1 , wherein the first and second angularly inclined arms are joined at the proximal lower end by a vertically extending mounting portion to form a Y-shaped tail support.

6 . The aircraft structure of claim 1 , wherein a span ratio is defined as a ratio of:

(a distance between a distal end of each angularly inclined arm)/(a total length of the rear wing span), and

wherein the span ratio of the aircraft structure is in a range of about 0.088 to 0.105.

7 . The aircraft structure of claim 1 , wherein the first and second angularly inclined arms are angularly offset relative to each other by about 19 to 26 degrees.

8 . The aircraft structure of claim 1 , wherein each wing has a fixed leading edge and a pivotal trailing control surface.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (28)