REAR END SECTION FOR AN AIRCRAFT

Abstract

A rear end section for an aircraft, having a fuselage, a v-tail, and a thruster assembly including at least one propulsion device installed to ingest and consume air forming a fuselage boundary layer, a control surface attached at the rearmost section of the rear end, and a casing covering at least part of the propulsion device such that an air inlet and an air outlet are defined between the casing and the propulsion device. The air inlet is configured to permit passage of the fuselage boundary layer towards the propulsion device. The air outlet is configured to direct the airflow exhausted from the propulsion device into the control surface, to divert the airflow and provide vectoring thrust for the aircraft.

Claims

1. A rear end section for an aircraft, comprising: a fuselage, a v-tail configuration, and a thruster assembly mounted on the rear end section fuselage between the v-tail configuration and the rearmost section of said rear end section fuselage, wherein the thruster assembly comprises: at least one propulsion device installed to ingest and consume air forming a fuselage boundary layer, a control surface attached at the rearmost section of the rear end section fuselage, and a casing covering at least part of the propulsion device such that an air inlet and an air outlet are defined between the casing and the propulsion device, the air inlet being configured to allow a passage of the fuselage boundary layer towards the propulsion device, and the air outlet being configured to direct an airflow exhausted from the propulsion device towards the control surface to divert said airflow and provide vectoring thrust for the aircraft.

2. The rear end section for an aircraft, according to claim 1, wherein the thruster assembly casing has a main surface substantially parallel to the rear end section fuselage, and wherein the casing further comprises at least one flap movable between two extreme positions, a close position wherein the flap is aligned with the main surface of the casing, and an open position wherein the flap is deflected, forming an angle with said main surface, to operate as an air-brake.

3. The rear end section for an aircraft, according to claim 1, wherein the control surface is rotatably attached to a rearmost section of the rear end section to provide a pitching movement to the aircraft.

4. The rear end section for an aircraft, according to claim 1, wherein the propulsion device comprises engine driving fluid mechanical devices.

5. The rear end section for an aircraft according to claim 4, wherein the engine driving fluid mechanical devices comprise fans.

6. The rear end section for an aircraft according to claim 4, wherein the engine driving fluid mechanical devices comprise or paddles.

7. The rear end section for an aircraft according to claim 4, wherein the engine driving fluid mechanical devices comprise electroaerodynamic devices.

8. The rear end section for an aircraft according to claim 7, wherein the electroaerodynamic devices comprise electromagnetic actuators.

9. The rear end section for an aircraft according to claim 7, wherein the electroaerodynamic devices comprise plasma-dynamic actuators.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0015] For a better comprehension of the invention, the following drawings are provided for illustrative and non-limiting purposes, wherein:

[0016] FIG. 1 shows a perspective view of the aircraft rear end section of the aircraft.

[0017] FIG. 2 shows an upper perspective view of the rear end section of the aircraft.

[0018] FIG. 3 shows a schematic longitudinal section view of the rear end section of the aircraft.

[0019] FIG. 4 shows a rear view of the rear end section of the aircraft.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0020] FIG. 1 shows a preferred embodiment of the proposed concept. A conventional fuselage is shaped so that its rear end fuselage (4) section has a flattened shape. A thruster assembly (3) is installed towards the end of the fuselage (4), between the fins of a v-tail (2) arrangement and the rearmost section of the rear end fuselage (4).

[0021] As seen in FIG. 2, the thruster assembly (3) comprises at least one propulsion device (5), a control surface (6), and a casing (7) defining an air inlet (8) and an air outlet (9) between the casing (7) and the propulsion device (5).

[0022] The propulsion device (5) is installed to ingest and consume air forming the fuselage boundary layer. The control surface (6) is mounted at the rearmost section of the rear end to receive the exhaust (outflow) of the propulsion device (5), and thus provide vectoring thrust to the aircraft when the control surface (6) is deflected. The casing (7) is designed to cover at least part of the propulsion device (5) to allow both the passage of the fuselage boundary layer towards the propulsion device (5) through the air inlet (8), and the passage of the airflow exhausted from the propulsion device (5) towards the control surface (6) through the air outlet (9).

[0023] As shown in FIG. 3 and according to a preferred embodiment, the thruster assembly casing (7) has a main surface (10) substantially parallel to the aircraft fuselage (4), and the casing (7) further comprises at least one flap (11) movable between two extreme positions, a close position wherein the flap (11) is aligned with the main surface (10) of the casing (7), and an open position wherein the flap (11) is deflected, forming an angle with the main surface (10), to operate as an air-brake.

[0024] According to another preferred embodiment, the control surface (6) is rotatably attached to the rearmost section of the rear end to provide a pitching movement to the aircraft. The technical advantage of this vectored thrust is to reduce the size of the empennage.

[0025] Finally, as shown in FIGS. 2-4 and according to another preferred embodiment, the propulsion device (5) comprises an engine driving fluid mechanical devices, such as fans (13) or paddles (12), or electroaerodynamic devices, such as electromagnetic or plasma-dynamic actuators.

[0026] 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.