Electromechanically actuated control rod for flight vehicles

Patent metadata

Field	Value
Publication number	US-11548620-B2
Application number	US-202016807547-A
Country	US
Kind code	B2
Filing date	Mar 3, 2020
Priority date	Mar 11, 2019
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A control rod assembly is provided for moving a control surface of a flight vehicle. The control rod assembly includes a first connector for connecting to a first structure of vehicle, and a second connector for connecting to a second structure of the vehicle. A connecting rod may be operably coupled between the first and second connectors, and an actuator may be operably coupled to the connecting rod. The actuator may include a screw-and-nut assembly, and a motor that is configured to drive the screw-and-nut assembly. The actuator may be operable such that driving the screw-and-nut assembly via the motor causes the connecting rod to translate linearly along a longitudinal axis to thereby vary a distance between the first and second connectors. The actuators may be electromechanical actuators which may be controlled by a controller without pilot interaction. Two such actuators may be provided on opposite sides of the assembly.

First claim

What is claimed is:

1. A flight vehicle control rod assembly for moving a control surface of a flight vehicle, comprising:
a first connector for connecting to a first structure of the flight vehicle;
a second connector for connecting to a second structure of the flight vehicle;
a connecting rod operably coupled between the first and second connectors; and
an actuator operably coupled to the connecting rod, the actuator including a screw-and-nut assembly mounted with respect to the connecting rod, and a motor that is configured to drive the screw-and-nut assembly;
wherein the actuator is operable such that driving the screw-and-nut assembly via the motor causes the connecting rod to translate linearly along a longitudinal axis to thereby vary a distance between the first and second connectors.

2. The flight vehicle control rod assembly according to claim 1 ,
wherein the motor and screw-and-nut assembly are contained within a housing of the actuator; and
wherein the connecting rod is linearly movable relative to the housing along the longitudinal axis.

3. The flight vehicle control rod assembly according to claim 1 ,
wherein the housing includes an opening at a first end portion thereof that receives an end portion of the connecting rod, the connecting rod being extendable or retractable with respect of the housing via the opening; and
wherein the housing includes the first connector at a second end portion thereof that is opposite the first end portion.

4. The flight vehicle control rod assembly according to claim 1 ,
wherein the motor is a direct drive electric motor that is operable to drive the screw-and-nut assembly.

5. The flight vehicle control rod assembly according to claim 1 ,
wherein the nut-and-screw assembly is a ballscrew-and-ballnut assembly including a ballscrew and a ballnut;
wherein the ballscrew is rotatably drivable by the motor; and
wherein the ballnut is linearly translatable along the ballscrew, the ballnut being operatively coupled to the connecting rod such that driving the ball screw via the motor causes the connecting rod to linearly translate with the ball nut.

6. The flight vehicle control rod assembly according to claim 5 , wherein the motor is a brushless DC direct drive motor, and wherein an output shaft of the motor is unitary with the ballscrew.

7. The flight vehicle control rod assembly according to claim 1 ,
wherein the actuator includes an electromechanical brake including a solenoid and a brake mechanism configured to permit or restrict rotation of an output shaft of the motor;
wherein, when the solenoid is energized, the electromechanical brake is in a disengaged state such that the brake mechanism permits rotation of the output shaft; and
wherein, when the solenoid is de-energized, the electromechanical brake is in an engaged state such that the brake mechanism restricts rotation of the output shaft.

8. The flight vehicle control rod assembly according to claim 1 , wherein the actuator includes a position sensor for sensing a position of a portion of the connecting rod relative to a portion of the actuator.

9. The flight vehicle control rod assembly according to claim 1 , wherein the actuator includes an electronic controller configured to control the motor.

10. The flight vehicle control rod assembly according to claim 9 , wherein the electronic controller is mounted onboard the control rod assembly, or wherein the electronic controller is located remotely of the control rod assembly.

11. The flight vehicle control rod assembly according to claim 1 , further comprising one or more stops for holding a position of the connecting rod relative to the first or second connector.

12. The flight vehicle control rod assembly according to claim 11 ,
wherein the one or more stops include one or more mechanical stops or one or more electrical stops.

13. The flight vehicle control rod assembly according to claim 1 ,
wherein the actuator is a first actuator disposed at a first end portion of the control rod assembly; and
wherein the control rod assembly includes a second actuator disposed at a second end portion of the control rod assembly opposite the first end portion.

14. The flight vehicle control rod assembly according to claim 1 ,
wherein the screw-and-nut assembly includes a power screw and a nut, the nut being operably coupled within a hollow internal portion of the connecting rod, the power screw being rotatable and the nut being translatable, and wherein the power screw is extendible or retractable relative to the hollow internal portion via the nut.

15. The flight vehicle control rod assembly according to claim 2 , wherein the screw-and-nut assembly includes a power screw and a nut, the nut being operably coupled to the connecting rod, the power screw being rotatable and the nut being translatable, and wherein the nut includes an anti-rotation trunnion having a roller that is guidably movable in a groove of the housing of the actuator.

16. The flight vehicle control rod assembly according to claim 3 , wherein the first end portion of the housing of the actuator includes a seal and/or a scraper.

17. A flight vehicle control rod assembly comprising:
a connecting rod,
a first end portion having a first actuator that is operably coupled to the connecting rod and operative to extend, retract, or hold a first portion of the connecting rod relative to the first actuator,
a second end portion opposite the first end portion having a second actuator that is operably coupled to the connecting rod and operative to extend, retract, or hold a second portion of the connecting rod relative to the second actuator,
wherein the first and second actuators are electromechanical actuators that each include an electric motor, a ballscrew, and a ballnut;
wherein the ballscrew is operably coupled to the electric motor for being rotated about an axis by the electric motor;
wherein the ballnut is operably coupled to the connecting rod for common axial movement together; and
wherein the ballscrew and connecting rod are linearly translatable in a direction of the axis in response to rotation of the ballscrew via the electric motor.

18. A rotor assembly of a helicopter, comprising:
a plurality of rotor blades having respective control surfaces;
a swashplate assembly operably coupled to the plurality of blades;
a control rod assembly operably coupled to the swashplate assembly to effect movement of the control surfaces;
wherein the control rod assembly includes:
a first connector operably coupled to the swashplate, and a second connector operably coupled to another structure of the helicopter;
a connecting rod operably coupled between the first and second connectors; and
an actuator operably coupled to the connecting rod, the actuator being configured to adjust a position of the connecting rod to vary a distance between the first and second connectors.

19. A flight vehicle control system of a flight vehicle having a control surface, the flight vehicle control system comprising:
an electronic flight controller; and
the control rod assembly according to claim 1 , operably coupled to the flight controller;
wherein the control rod assembly is operable to move the control surface of the flight vehicle independently of human pilot interaction.

Assignees

• Parker Hannifin Corp

Inventors

• Charafeddine Abbas M
• Edwards David E

Classifications

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C13/50 Primary

  using electrical energy · CPC title

• B64C27/605 Primary

  including swash plate, spider or cam mechanisms · CPC title

• F16H25/2204

  with balls · CPC title

• Y02T50/40

  Weight reduction · CPC title