Tiltrotor with Inboard Engines

• US 20170158323A1
• Filed: 12/07/2015
• Published: 06/08/2017
• Est. Priority Date: 12/07/2015
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Ross, Brent C., Ivans, Steven R.
• Granted Patent: US 10,183,745 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/185 Spars
• CPC Class Codes: B64C 3/187 Ribs
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 35/08 characterised by the transmission being driven by a plurality of power plants

Abstract

According to one embodiment, an aircraft features a fuselage, a wing coupled to the fuselage, and a first rotor system. The first rotor system includes a first proprotor system and a first engine. The first proprotor system is coupled proximate to a first wing tip of the wing and is tiltable between a helicopter mode position and an airplane mode position. The first engine is in mechanical communication with the first proprotor system and coupled above the wing, outboard of the fuselage and inboard of the first pylon.

Claims

1. An aircraft, comprising:

a fuselage;

a wing coupled to the fuselage;

a first rotor system coupled to the wing, the first rotor system comprising;

a first proprotor system coupled proximate to a first wing tip of the wing, the first proprotor system being tiltable between a helicopter mode position and an airplane mode position; and

a first engine in mechanical communication with the first proprotor system and coupled above the wing, outboard of the fuselage and inboard of the first pylon.

2. The aircraft of claim 1, further comprising a second rotor system coupled to the wing, the second rotor system comprising:

a second pylon coupled proximate to a second wing tip of the wing opposite the first wing tip, the second pylon being tiltable between a helicopter mode position and an airplane mode position; and

a second engine in mechanical communication with the second proprotor system and coupled above the wing, outboard of the fuselage and inboard of the second pylon.

3. The aircraft of claim 2, wherein the first and second engines are fixed relative to the wing.

4. The aircraft of claim 2, further comprising one or more interconnect drive shafts in mechanical communication with the first and second engines.

5. The aircraft of claim 4, further comprising:

a first gearbox in mechanical communication with the first engine, the first proprotor system, and the one or more interconnect drive shafts; and

a second gearbox in mechanical communication with the second engine, the second proprotor system, and the one or more interconnect drive shafts.

6. The aircraft of claim 5, wherein the first and second gearboxes are fixed relative to the wing.

7. The aircraft of claim 5, wherein:

the first gearbox comprises a first accessory gear portion configured to transmit mechanical energy to a first accessory device; and

the second gearbox comprises a second accessory gear portion configured to transmit mechanical energy to a second accessory device.

8. The aircraft of claim 7, wherein the first accessory device is a generator or a pump.

9. The aircraft of claim 5, wherein:

the first gearbox is in mechanical communication between the first engine and the first proprotor system; and

the second gearbox is in mechanical communication between the second engine and the second proprotor system.

10. The aircraft of claim 5, wherein the first gearbox is located inboard of the first proprotor system and the second gearbox is located inboard of the second proprotor system.

11. The aircraft of claim 5, the wing comprising:

a first wing spar;

a second wing spar;

a first wing rib coupled and substantially perpendicular to the first and second wing spars; and

a second wing rib coupled and substantially perpendicular to the first and second wing spars, wherein;

the first wing spar, the second wing spar, the first wing rib, and the second wing rib form, in combination, a torque box; and

the first gearbox is positioned adjacent to and about the first wing spar such that the first gearbox does not intrude into the torque box.

12. The aircraft of claim 5, the first gearbox comprising:

an interconnect driveshaft gear configured to communicate mechanical energy between the first gearbox and the one or more interconnect driveshafts;

one or more accessory gears coplanar with and in mechanical communication with the interconnect driveshaft gear;

a proprotor gear located inboard of the first proprotor system, the proprotor gear being coplanar with and in mechanical communication with the interconnect driveshaft gear and the one or more accessory gears, the proprotor gear configured to communicate mechanical energy to the first proprotor system; and

an engine gear coplanar with and in mechanical communication with the interconnect driveshaft gear, the one or more accessory gears, and the proprotor gear, the engine gear configured to transmit mechanical energy from the first engine to the first proprotor system via the proprotor gear.

13. The aircraft of claim 5, wherein:

the first proprotor system is in mechanical communication between the first engine and the first gearbox; and

the second proprotor system is in mechanical communication between the second engine and the second gearbox.

14. The aircraft of claim 5, wherein the first gearbox is located outboard of the first proprotor system and the second gearbox is located outboard of the second proprotor system.

15. The aircraft of claim 5, wherein the first gearbox receives mechanical energy from the first engine via the first proprotor system.

16. The aircraft of claim 5, the first gearbox comprising:

an interconnect driveshaft gear configured to communicate mechanical energy between the first gearbox and the one or more interconnect driveshafts;

one or more accessory gears coplanar with and in mechanical communication with the interconnect driveshaft gear;

a proprotor gear located outboard of the first proprotor system, the proprotor gear being coplanar with and in mechanical communication with the interconnect driveshaft gear and the one or more accessory gears, the proprotor gear in mechanical communication with the first proprotor system;

one or more proprotor shafts coupled to the proprotor gear and passing through the first proprotor system; and

an engine gear coupled to the one or more proprotor shafts and configured to provide mechanical energy from the first engine to the first proprotor system and the proprotor gear.