Aircraft having radially extendable tailboom assembly

Patent metadata

Field	Value
Publication number	US-10287012-B2
Application number	US-201615241436-A
Country	US
Kind code	B2
Filing date	Aug 19, 2016
Priority date	Aug 19, 2016
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

First claim

What is claimed is:

1. A tail sitter aircraft comprising:
a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis;
a main lifting surface supported by the forward portion of the fuselage;
a propulsion system operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing;
a tailboom assembly extending from the aft portion of the fuselage, the tailboom assembly including a plurality of rotatably mounted tail arms having control surfaces and landing members; and
an actuator assembly operable to transition the tail arms between a forward flight configuration and a landing configuration, the actuator assembly including at least one rotary actuator;
wherein, in the forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces; and
wherein, in the landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

2. The tail sitter aircraft as recited in claim 1 wherein the main lifting surface further comprises at least three generally circumferentially distributed wings.

3. The tail sitter aircraft as recited in claim 1 wherein the propulsion system further comprises a distributed propulsion system.

4. The tail sitter aircraft as recited in claim 1 wherein the propulsion system further comprises a plurality of cross-flow fans.

5. The tail sitter aircraft as recited in claim 1 wherein the propulsion system further comprises a plurality of variable thrust cross-flow fans.

6. The tail sitter aircraft as recited in claim 1 wherein the tailboom assembly further comprises at least three rotatably mounted tail arms.

7. The tail sitter aircraft as recited in claim 1 wherein the actuator assembly further comprises at least one linear actuator.

8. The tail sitter aircraft as recited in claim 1 wherein the actuator assembly further comprises a locking system operable to secure the tail arms in at least one of the forward flight configuration and the landing configuration.

9. A tail sitter aircraft comprising:
a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis;
at least three generally circumferentially distributed wings supported by the forward portion of the fuselage, the wings providing a main lifting surface;
a distributed propulsion system operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing; and
a tailboom assembly extending from the aft portion of the fuselage, the tailboom assembly including a plurality of rotatably mounted tail arms having control surfaces and landing members;
wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces; and
wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

10. The tail sitter aircraft as recited in claim 9 wherein the tailboom assembly further comprises at least three rotatably mounted tail arms.

11. The tail sitter aircraft as recited in claim 9 wherein the distributed propulsion system further comprises a plurality of cross-flow fans.

12. The tail sitter aircraft as recited in claim 9 wherein the distributed propulsion system further comprises a plurality of variable thrust cross-flow fans.

13. The tail sitter aircraft as recited in claim 9 wherein the tailboom assembly further comprises an actuator assembly operable to transition the tail arms between the forward flight configuration and the landing configuration.

14. The tail sitter aircraft as recited in claim 13 wherein the actuator assembly further comprises at least one linear actuator.

15. The tail sitter aircraft as recited in claim 13 wherein the actuator assembly further comprises at least one rotary actuator.

16. The tail sitter aircraft as recited in claim 13 wherein the actuator assembly further comprises a locking system operable to secure the tail arms in at least one of the forward flight configuration and the landing configuration.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Robertson Daniel Bryan
• Groninga Kirk Landon
• Fenny Carlos Alexander

Classifications

• B64U70/80

  Vertical take-off or landing, e.g. using rockets (rotorcrafts B64U10/10; VTOL aircraft B64U10/20) · CPC title

• B64U50/14

  ducted or shrouded · CPC title

• B64C11/006

  Paddle wheels · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C25/16

  Fairings movable in conjunction with undercarriage elements · CPC title