Tip gap control systems with active blade tips

Patent metadata

Field	Value
Publication number	US-11370536-B2
Application number	US-202016907071-A
Country	US
Kind code	B2
Filing date	Jun 19, 2020
Priority date	Jun 19, 2020
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

First claim

What is claimed is:

1. A tip gap monitoring and control system for a ducted aircraft having a vertical takeoff and landing flight mode and a forward flight mode, the tip gap monitoring and control system comprising:
a flight control computer comprising:
a tip gap monitoring system including one or more sensors; and
a blade length control module configured to generate a blade tip actuator command in response to the aircraft converting between the vertical takeoff and landing flight mode and the forward flight mode; and
a proprotor system in data communication with the flight control computer, the proprotor system comprising:
a duct;
a plurality of proprotor blades surrounded by the duct, each of the proprotor blades including an active blade tip movable into a plurality of positions including a retracted position and an extended position; and
one or more actuators coupled to the active blade tips;
wherein, the tip gap monitoring system is configured to monitor a tip gap between the proprotor blades and the duct; and
wherein, the one or more actuators are configured to move the active blade tips between the retracted position and the extended position based on the blade tip actuator command, thereby controlling the tip gap between the proprotor blades and the duct.

2. The tip gap monitoring and control system as recited in claim 1 wherein the blade tip actuator command further comprises a tip gap adjustment distance, the one or more actuators configured to move the active blade tips by the tip gap adjustment distance.

3. The tip gap monitoring and control system as recited in claim 1 wherein the blade tip actuator command further comprises one or more blade-specific blade tip actuator commands, each of the one or more blade-specific blade tip actuator commands corresponding to a respective one of the active blade tips.

4. The tip gap monitoring and control system as recited in claim 1 wherein each of the proprotor blades further comprises a main body having an open distal end, the active blade tips slidably coupled to the open distal ends of the main bodies of the proprotor blades; and
wherein, the active blade tips are at least partially retracted into the main bodies of the proprotor blades in the retracted position and at least partially extended from the open distal ends of the main bodies of the proprotor blades in the extended position, thereby increasing the tip gap in the retracted position.

5. The tip gap monitoring and control system as recited in claim 1 wherein each of the proprotor blades further comprise a main body having a distal end, the active blade tips hingeably coupled to the distal ends of the main bodies of the proprotor blades; and
wherein, the active blade tips are substantially coplanar with the main bodies of the proprotor blades in the extended position and form an angle of less than 180 degrees with the main bodies of the proprotor blades in the retracted position, thereby increasing the tip gap in the retracted position.

6. The tip gap monitoring and control system as recited in claim 1 wherein each proprotor blade further comprises a spring biasing a respective active blade tip in one of the retracted position or the extended position.

7. The tip gap monitoring and control system as recited in claim 1 wherein the active blade tips are independently actuated to permit nonuniform positioning of the active blade tips.

8. The tip gap monitoring and control system as recited in claim 1 wherein the proprotor system further comprises a proprotor hub, the one or more actuators disposed at the proprotor hub; and
wherein, the one or more actuators are coupled to the active blade tips by a plurality of spanwise links.

9. The tip gap monitoring and control system as recited in claim 1 wherein the one or more actuators further comprise a plurality of actuators disposed at distal ends of the proprotor blades, each actuator coupled to a respective one of the active blade tips.

10. The tip gap monitoring and control system as recited in claim 1 wherein the one or more sensors are coupled to the proprotor system; and
wherein, the one or more sensors include at least one of a strain gauge, an accelerometer or a distance sensor.

11. A rotorcraft having a vertical takeoff and landing flight mode and a forward flight mode, the rotorcraft comprising:
a fuselage;
a flight control computer comprising:
a tip gap monitoring system including one or more sensors; and
a blade length control module configured to generate a blade tip actuator command in response to the rotorcraft converting between the vertical takeoff and landing flight mode and the forward flight mode; and
a proprotor system coupled to the fuselage and in data communication with the flight control computer, the proprotor system comprising:
a duct;
a plurality of proprotor blades surrounded by the duct, each of the proprotor blades including an active blade tip movable into a plurality of positions including a retracted position and an extended position; and
one or more actuators coupled to the active blade tips;
wherein, the tip gap monitoring system is configured to monitor a tip gap between the proprotor blades and the duct; and
wherein, the one or more actuators are configured to move the active blade tips between the retracted position and the extended position based on the blade tip actuator command, thereby controlling the tip gap between the proprotor blades and the duct.

12. The rotorcraft as recited in claim 11 further comprising a maneuver detection module configured to detect a flight condition of the rotorcraft, the blade length control module configured to determine the blade tip actuator command based on the flight condition;
wherein, the flight condition further comprises at least one of a flight maneuver or a flight mode.

13. A method for controlling a tip gap for a ducted aircraft having a vertical takeoff and landing flight mode and a forward flight mode, the method comprising:
monitoring a tip gap between a duct and a plurality of proprotor blades using one or more sensors;
generating a blade tip actuator command in response to the ducted aircraft converting between the vertical takeoff and landing flight mode and the forward flight mode;
transmitting the blade tip actuator command to a proprotor system including the duct and the proprotor blades, the proprotor blades including active blade tips; and
moving at least one of the active blade tips between a retracted position and an extended position in response to the blade tip actuator command, thereby controlling the tip gap between the proprotor blades and the duct.

14. The method as recited in claim 13 further comprising generating the blade tip actuator command in response to receiving a tip gap adjustment distance.

15. The method as recited in claim 14 further comprising generating the blade tip actuator command in response to the tip gap adjustment distance exceeding a tip gap adjustment distance threshold.

16. The method as recited in claim 13 further comprising generating the blade tip actuator command based on a pitch of the proprotor blades.

17. The method as recited in claim 13 further comprising retracting the active blade tips in response to detecting a structural deformity of the proprotor system.

18. The method as recited in claim 13 further comprising retracting the active blade tips in response to detecting a collision with the proprotor system.

19. The method as recited in claim 13 further comprising moving the active blade tips such t

Assignees

• Textron Innovations Inc

Inventors

• Knoll Jonathan Andrew
• Thompson George Matthew
• Carlson Nicholas Ralph

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64C11/003

  Variable-diameter propellers; Mechanisms therefor · CPC title

• B64C11/32

  mechanical · CPC title

• B64C11/001 Primary

  Shrouded propellers · CPC title