Vertical take-off and landing multirotor aircraft with at least eight thrust producing units
US-2020164972-A1 · May 28, 2020 · US
Fixed wing aircraft with trailing rotors and T-tail
US12515792B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12515792-B2 |
| Application number | US-202519062829-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 25, 2025 |
| Priority date | Aug 2, 2019 |
| Publication date | Jan 6, 2026 |
| Grant date | Jan 6, 2026 |
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- Title
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- Abstract
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- First independent claim
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Abstract
Official abstract text for this publication.
An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules, a dovetail, and a T-tail. The plurality of tilt rotor submodules are coupled to the trailing edge of the forward swept and fixed wing. The dovetail is attached to an underside of a fuselage. The T-tail is located above the dovetail. A horizontal plane of the T-tail is at a height that is higher than a horizonal plane of the forward swept and fixed wing.
First claim
Opening claim text (preview).
What is claimed is: 1 . An aircraft, comprising: a canard having a leading edge and a trailing edge; a forward swept and fixed wing having a trailing edge; a plurality of tilt rotor submodules that are coupled to the trailing edge of the forward swept and fixed wing; and a dovetail attached to an underside of a fuselage; and a T-tail located above the dovetail, wherein a horizontal plane of the T-tail is at a height that is higher than a horizonal plane of the forward swept and fixed wing; wherein the fuselage rests on the dovetail when the aircraft is on the ground. 2 . The aircraft of claim 1 , wherein the horizontal plane of the forward swept and fixed wing is at a height that is higher than a horizontal plane of the canard. 3 . The aircraft of claim 1 , wherein the plurality of tilt rotor submodules includes two tilt rotor submodules that are coupled to the canard and six tilt rotor submodules that are coupled to the forward swept and fixed wing. 4 . The aircraft of claim 1 , wherein the forward swept and fixed wing has a relative lifting force within a range of 80% to 100%, inclusive, during a cruise mode. 5 . The aircraft of claim 1 , wherein an inboard section of the forward swept and fixed wing has a twist angle within a range of −5° to 0°, inclusive. 6 . The aircraft of claim 1 , wherein a middle section of the forward swept and fixed wing has a twist angle within a range of 0° to 5°, inclusive. 7 . The aircraft of claim 1 , wherein an outboard section of the forward swept and fixed wing has a twist angle within a range of −5° to 0°, inclusive. 8 . The aircraft of claim 1 , wherein an outboard section of the forward swept and fixed wing stalls after the canard. 9 . The aircraft of claim 1 , wherein an outboard section of the forward swept and fixed wing stalls after the rest of the forward swept and fixed wing. 10 . The aircraft of claim 1 , wherein the T-tail is located at the height of 0.7 to 1.2 meters above a base of the aircraft. 11 . A method, comprising: providing a canard having a leading edge and a trailing edge; providing a forward swept and fixed wing having a trailing edge; providing a plurality of tilt rotor submodules that are coupled to the trailing edge of the forward swept and fixed wing; and providing a dovetail attached to an underside of a fuselage; and providing a T-tail located above the dovetail, wherein a horizontal plane of the T-tail is at a height that is higher than a horizonal plane of the forward swept and fixed wing; wherein the fuselage rests on the dovetail when the aircraft is on the ground. 12 . The method of claim 11 , wherein a horizontal plane of the forward swept and fixed wing is at a height that is higher than a horizontal plane of the canard. 13 . The method of claim 11 , wherein the plurality of tilt rotor submodules includes two tilt rotor submodules that are coupled to the canard and six tilt rotor submodules that are coupled to the forward swept and fixed wing. 14 . The method of claim 11 , wherein the forward swept and fixed wing has a relative lifting force within a range of 80% to 100%, inclusive, during a cruise mode. 15 . The method of claim 11 , wherein an inboard section of the forward swept and fixed wing has a twist angle within a range of −5° to 0°, inclusive. 16 . The method of claim 11 , wherein a middle section of the forward swept and fixed wing has a twist angle within a range of 0° to 5°, inclusive. 17 . The method of claim 11 , wherein an outboard section of the forward swept and fixed wing has a twist angle within a range of −5° to 0°, inclusive. 18 . The method of claim 11 , wherein an outboard section of the forward swept and fixed wing stalls after the canard. 19 . The method of claim 11 , wherein an outboard section of the forward swept and fixed wing stalls after the rest of the forward swept and fixed wing. 20 . The method of claim 11 , wherein the T-tail is located at the height of 0.7 to 1.2 meters above a base of the aircraft.
Assignees
Inventors
Classifications
Canard-type aircraft · CPC title
Tailplanes · CPC title
- B64C11/46Primary
Arrangements of, or constructional features peculiar to, multiple propellers {(B64C11/306 takes precedence)} · CPC title
Drag reduction · CPC title
using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title
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Frequently asked questions
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- What does patent US12515792B2 cover?
- An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules, a dovetail, and a T-tail. The plurality of tilt rotor submodules are coupled to the trailing edge of the forward swept and fixed wing. The dovetail is attached to an underside of a fuselage. The T-tail is located above the…
- Who is the assignee on this patent?
- Kitty Hawk Corp
- What technology area does this patent fall under?
- Primary CPC classification B64C11/46. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Jan 06 2026 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 5 related publications on this page (citations in our corpus or others sharing the same primary CPC).