Tilting ducted fan aircraft generating a pitch control moment

Patent metadata

Field	Value
Publication number	US-10106253-B2
Application number	US-201615252916-A
Country	US
Kind code	B2
Filing date	Aug 31, 2016
Priority date	Aug 31, 2016
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage having a forward portion and an aft portion;
first and second ducted fans supported by the forward portion of the fuselage and tiltable relative to the fuselage between a substantially horizontal orientation in a vertical takeoff and landing mode and a substantially vertical orientation in a forward flight mode;
a tailboom extending from the aft portion of the fuselage and having an aft station; and
a variable thrust cross-flow fan system disposed in the aft station of the tailboom operable to generate a pitch control moment, the variable thrust cross-flow fan system comprising:
a cross-flow fan assembly having a longitudinal axis and including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a substantially circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations; and
a control assembly coupled to the plurality of blades, the control assembly including a control cam operable to translate relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades;
wherein, the cross-flow fan assembly is operable to produce a thrust in one of a first or second direction in response to the control cam translating upward relative to the cross-flow fan assembly and is further operable to produce a thrust in the other of the first or second direction in response to the control cam translating downward relative to the cross-flow fan assembly, the first direction opposite from the second direction.

2. The aircraft as recited in claim 1 wherein the pitch control moment further comprises pitch control thrust generated by the variable thrust cross-flow fan system.

3. The aircraft as recited in claim 1 wherein the pitch control moment further comprises variable pitch control thrust generated by the variable thrust cross-flow fan system.

4. The aircraft as recited in claim 1 wherein the pitch control moment further comprises reversible pitch control thrust generated by the variable thrust cross-flow fan system.

5. The aircraft as recited in claim 1 wherein the pitch control moment is operable to maintain the aircraft in a substantially horizontal attitude during hover.

6. The aircraft as recited in claim 1 wherein the pitch control moment is operable to maintain the aircraft in a substantially horizontal attitude during transitions between the vertical takeoff and landing mode and the forward flight mode.

7. The aircraft as recited in claim 1 wherein the plurality of pitch angle configurations includes at least one upward thrust configuration, a neutral configuration and at least one downward thrust configuration.

8. The aircraft as recited in claim 1 wherein the control cam is operable to rotate with the cross-flow fan assembly.

9. The aircraft as recited in claim 1 wherein the control cam is non-rotatable relative to the cross-flow fan assembly.

10. The aircraft as recited in claim 1 wherein, in vertical takeoff and landing mode, yaw is controllable responsive to thrust vectoring the first and second ducted fans.

11. The aircraft as recited in claim 1 wherein, in vertical takeoff and landing mode, roll is controllable responsive to independently adjusting collective pitch of the first and second ducted fans.

12. The aircraft as recited in claim 1 wherein, in forward flight mode, yaw is controllable responsive to independently adjusting collective pitch of the first and second ducted fans.

13. An aircraft comprising:
a fuselage having a forward portion and an aft portion;
first and second ducted fans supported by the forward portion of the fuselage and tiltable relative to the fuselage between a substantially horizontal orientation in a vertical takeoff and landing mode and a substantially vertical orientation in a forward flight mode;
a tailboom extending from the aft portion of the fuselage and having first and second aft stations;
a first variable thrust cross-flow fan system disposed in the first aft station of the tailboom operable to generate a pitch control moment; and
a second variable thrust cross-flow fan system disposed in the second aft station of the tailboom operable to generate a yaw control moment, the first and second variable thrust cross-flow fan systems each comprising:
a cross-flow fan assembly having a longitudinal axis and including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a substantially circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations; and
a control assembly coupled to the plurality of blades, the control assembly including a control cam operable to translate relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades;
wherein, the cross-flow fan assembly of the first variable thrust cross-flow fan system is operable to produce a thrust in one of an upward or downward direction in response to the control cam translating upward relative to the cross-flow fan assembly and is further operable to produce a thrust in the other of the upward or downward direction in response to the control cam translating downward relative to the cross-flow fan assembly; and
wherein, the cross-flow fan assembly of the second variable thrust cross-flow fan system is operable to produce a thrust in one of a leftward or rightward direction in response to the control cam translating leftward relative to the cross-flow fan assembly and is further operable to produce a thrust in the other of the leftward or rightward direction in response to the control cam translating rightward relative to the cross-flow fan assembly.

14. The aircraft as recited in claim 13 wherein the first aft station is aft of the second aft station.

15. The aircraft as recited in claim 13 wherein the pitch control moment further comprises a reversible pitch control thrust generated by the first variable thrust cross-flow fan system and wherein the yaw control moment further comprises a reversible yaw control thrust generated by the second variable thrust cross-flow fan system.

16. The aircraft as recited in claim 1 further comprising:
an actuator assembly operably coupled to the control cam, the actuator assembly operable to translate the control cam relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades to generate variable thrust.

17. The aircraft as recited in claim 1 wherein the cross-flow fan assembly is operable to rotate at a substantially constant rotational speed.

18. The aircraft as recited in claim 1 wherein the control cam forms one or more follower slots.

19. The aircraft as recited in claim 18 wherein the one or more follower slots further comprise one or more concentric follower slots.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Groninga Kirk Landon
• Robertson Daniel Bryan

Classifications

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C27/82 Primary

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C2027/8254

  Shrouded tail rotors, e.g. "Fenestron" fans · CPC title

• B64C2027/8245

  using air jets · CPC title

• B64C39/008

  about a longitudinal axis · CPC title