ASYMMETRIC AIRCRAFT CONFIGURATION

Abstract

An asymmetric aircraft configuration having a first and a second wing, the first wing having a span larger than the second wing. A first engine is mounted on the first wing, and a second engine mounted on the rear end of the aircraft with its centerline aligned with the aircraft longitudinal axis. The rear end of the aircraft has a T tail, and the second engine is configured to ingest and consume air forming a boundary layer during the flight. A main landing gear assembly includes a first landing gear attached to the first wing, and a second landing gear attached to an area of the fuselage close to the second wing.

Claims

1. An asymmetric configuration for an aircraft comprising: a first wing and a second wing, the first wing having a span larger than the second wing, a first engine mounted on the first wing of the aircraft, and a second engine mounted on a rear end of the aircraft with its centerline aligned with a longitudinal axis of the aircraft, the rear end of the aircraft having a T tail, and the second engine having a casing defining a forward inlet configured to ingest a boundary layer during a flight, and an aft outlet to discharge an exhaust of the second engine, and a main landing gear assembly comprising a first landing gear attached to the first wing, and a second landing gear attached to an area of a fuselage close to the second wing.

2. The asymmetric aircraft configuration, according to claim 1, wherein the first wing comprises a root section attached to the fuselage, and a tip section extending outwardly from the root section, the root section having a sweep angle different than the tip section.

3. The asymmetric aircraft configuration, according to claim 2, wherein the first engine is mounted on an interface between the root section and the tip section.

4. The asymmetric aircraft configuration, according to claim 2, wherein the tip section has the same size as the second wing.

5. The asymmetric aircraft configuration, according to claim 2, wherein the tip section has a foldable tip.

6. The asymmetric aircraft configuration, according to claim 2, wherein the first landing gear is attached to a rear spar of the root section of the first wing.

7. The asymmetric aircraft configuration, according to claim 2, wherein the first wing is configured to receive the first landing gear when retracted.

8. The asymmetric aircraft configuration, according to claim 2, wherein the fuselage is configured to receive the first landing gear when retracted.

9. The asymmetric aircraft configuration, according to claim 2, wherein the aircraft has a ventral fairing configured to receive the second landing gear when retracted.

10. The asymmetric aircraft configuration, according to claim 1, wherein the first engine is mounted over or under the first wing of the aircraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0017] For a better comprehension of the invention, the following drawings are provided for illustrative and non-limiting purposes, wherein:

[0018] FIG. 1 shows a first state of the art aircraft configuration.

[0019] FIG. 2 shows a second state of the art aircraft configuration.

[0020] FIG. 3 shows a third state of the art aircraft configuration.

[0021] FIG. 4 shows a perspective view of the asymmetric aircraft configuration, according to a preferred embodiment of the invention.

[0022] FIG. 5 shows a front view of the aircraft shown in FIG. 4.

[0023] FIG. 6 shows a plant view of the aircraft shown in FIG. 4 and FIG. 5.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] FIG. 4 shows an asymmetric aircraft configuration having a first (3′, 3″) and a second wing (4), the first wing (3′, 3″) having a span larger than the second wing (4). As shown, the first wing (3′, 3″) preferably comprises a root section (3′) attached to the fuselage, and a tip section (3″) extending outwardly from the root section (3′), the root section (3′) having a sweep angle different than the tip section (3″).

[0025] The aircraft has a T tail (14) configuration, and has two engines, a first engine (1) mounted on the first wing (3′, 3″) of the aircraft, and a second engine (2) mounted on the rear end of the aircraft. The first engine has to be installed on the first wing, since it has a larger span, in order to balance the aircraft laterally.

[0026] The second engine (2) has its centerline (12) aligned with the longitudinal axis of the aircraft, and has a casing (5) defining a forward inlet (6) designed to ingest a boundary layer during the flight, and an aft outlet (7) to allow the exhaust of the second engine (2).

[0027] The first engine (1) may be installed on the starboard wing to take advantage of the fact that this side of the aircraft is not accessed by passengers during boarding and disembarking operations.

[0028] As shown in FIG. 5, the aircraft has a main landing gear assembly comprising a first landing gear (8) attached to the first wing (3′, 3″), and a second landing gear (9) attached to an area of the fuselage close to the second wing (4).

[0029] According to a preferred embodiment, the first landing gear (8) is attached to the rear spar of the root section (3′) of the first wing (3′, 3″).

[0030] According to another preferred embodiment, the first wing (3′, 3″) is configured to receive the first landing gear (8) when retracted.

[0031] Alternatively, and according to another preferred embodiment, the fuselage is configured to receive the first landing gear (8) when retracted.

[0032] According to another preferred embodiment, the aircraft has a ventral fairing (11) configured to receive the second landing gear (9) when retracted.

[0033] As shown in FIG. 5, the tip section (3″) of the second wing has a foldable tip (10). This will enable extending the wing span to achieve desired performance characteristics without compromising the ability to park the aircraft in standard airport parking aprons.

[0034] As shown in FIGS. 4-6, the first engine (1) is preferably mounted on the interface between the root (3′) and tip sections (3″).

[0035] According to another preferred embodiment, the tip section (3″) has the same size (chord and span) as the second wing (4).

[0036] Finally, according to another preferred embodiment, the first engine (1) is mounted over or under the first wing (3′, 3″) of the aircraft.

[0037] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.