Compound Helicopters having Auxiliary Propulsive Systems

Patent metadata

Field	Value
Publication number	US-2021276703-A1
Application number	US-202117330281-A
Country	US
Kind code	A1
Filing date	May 25, 2021
Priority date	Mar 26, 2019
Publication date	Sep 9, 2021
Grant date	—

Abstract

A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

First claim

What is claimed is:

1 . A fully compounding rotorcraft comprising:
a fuselage; first and second wings coupled to the fuselage and configured to provide lift compounding responsive to forward airspeed; a twin boom including a first tail boom member extending aftward from a mid-wing location of the first wing and a second tail boom member extending aftward from a mid-wing location of the second wing, the first and second tail boom members each having aft ends; an empennage coupled between the aft ends of the first and second tail boom members, the empennage having a high boom tail configuration; an anti-torque system including a tail rotor rotatably coupled to the empennage; an engine disposed within the fuselage and configured to provide torque to an output shaft; a main rotor gearbox coupled to the output shaft; a main rotor assembly coupled to the main rotor gearbox and configured to receive torque from the engine; and first and second ducted fans configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor assembly during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft; wherein, the first ducted fan is coupled to at least one of the fuselage or the first tail boom member; and wherein, the second ducted fan is coupled to at least one of the fuselage or the second tail boom member.

2 . The fully compounding rotorcraft as recited in claim 1 wherein the rotorcraft is a helicopter.

3 . The fully compounding rotorcraft as recited in claim 1 wherein the first and second wings further comprise aft swept wings.

4 . The fully compounding rotorcraft as recited in claim 1 wherein the empennage further comprises first and second generally vertical stabilizers and a horizontal stabilizer coupled between the first and second generally vertical stabilizers.

5 . The fully compounding rotorcraft as recited in claim 4 wherein the first and second generally vertical stabilizers each further comprise a moveable control surface.

6 . The fully compounding rotorcraft as recited in claim 4 wherein the horizontal stabilizer further comprises at least one moveable control surface.

7 . The fully compounding rotorcraft as recited claim 4 wherein the first and second ducted fans are positioned below the horizontal stabilizer.

8 . The fully compounding rotorcraft as recited claim 4 wherein a thrust line of the first ducted fan is inline with at least a portion of the first vertical stabilizer and wherein a thrust line of the second ducted fan is inline with at least a portion of the second vertical stabilizer.

9 . The fully compounding rotorcraft as recited claim 1 wherein the first ducted fan is positioned between the first tail boom member and the fuselage and wherein the second ducted fan is positioned between the second tail boom member and the fuselage.

10 . The fully compounding rotorcraft as recited claim 1 wherein the first ducted fan is coupled between the first tail boom member and the fuselage and wherein the second ducted fan is coupled between the second tail boom member and the fuselage.

11 . The fully compounding rotorcraft as recited claim 1 wherein the first ducted fan is coupled to the first tail boom member and wherein the second ducted fan is coupled to the second tail boom member.

12 . The fully compounding rotorcraft as recited claim 1 wherein the first ducted fan is coupled to the fuselage and wherein the second ducted fan is coupled to the fuselage.

13 . The fully compounding rotorcraft as recited in claim 1 wherein the main rotor assembly further comprises a single main rotor having a plurality of rotor blades extending radially from a rotor hub.

14 . The fully compounding rotorcraft as recited claim 13 wherein the first and second ducted fans are positioned aft of the rotor hub.

15 . The fully compounding rotorcraft as recited claim 1 wherein the first and second ducted fans are positioned below the main rotor assembly.

16 . The fully compounding rotorcraft as recited claim 1 wherein the first and second ducted fans are positioned above the first and second wings.

17 . The fully compounding rotorcraft as recited claim 1 wherein the first and second ducted fans are positioned forward of the empennage.

18 . The fully compounding rotorcraft as recited claim 1 further comprising an electric generator disposed within the fuselage;
wherein the engine further comprises a turboshaft engine;
wherein the electric generator extracts power from the turboshaft engine during forward flight; and
wherein each of the first and second ducted fans includes at least one electric motor powered by the electric generator during forward flight.

19 . The fully compounding rotorcraft as recited claim 1 wherein the fuselage includes a tail cone and wherein the first and second ducted fans extend aft of the tail cone.

20 . The fully compounding rotorcraft as recited claim 1 further comprising a retractable tricycle landing gear system including a forward landing strut retractable into the fuselage, a first aft landing strut retractable into the first tail boom member and a second aft landing strut retractable into the second tail boom member.

Assignees

• Textron Innovations Inc

Inventors

• Ross Brent Chadwick
• Ewing Alan Carl
• Ivans Steven Ray

Classifications

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64C27/26 Primary

  characterised by provision of fixed wings · CPC title

• F02C3/10 Primary

  with another turbine driving an output shaft but not driving the compressor · CPC title