Actuator load path monitoring system

• US 8,033,500 B1
• Filed: 04/28/2008
• Issued: 10/11/2011
• Est. Priority Date: 04/28/2008
• Status: Active Grant

• Current Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Charafeddine, Abbas M., Delacotte, Vincent
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US12/150,365
• Time in Patent Office: 1,261 Days
• Field of Search: 244/75.1, 244/99.4, 244/99.3, 244/194
• US Class Current: 244/75.1
• CPC Class Codes: B64C 13/28 mechanical
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof

Abstract

An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure. The actuator is of a type including a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly; b) a ball screw assembly operatively connected to the gear assembly; c) a tie-rod assembly positioned within the ball screw assembly; and, d) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of the control surface. The actuator load path monitoring system includes an upper load sensing assembly positioned in an upper load path between the upper actuator assembly and the aircraft structure. The upper load sensing assembly provides upper indications of the applied forces in the upper load path when the upper load path is disconnected. A lower load sensing assembly is positioned in a lower load path between the lower actuator assembly and the control surface. The lower load sensing assembly provides upper indications of the applied forces in the lower load path when the lower load path is disconnected. A computer system receives the upper and lower indications of applied forces and analyzes the upper and lower indications, thereby monitoring the structural integrity and safety of the upper and lower load paths by annunciating the detection of a failed portion thereof.

Claims

1. An actuator system for an aircraft of a type having a primary aircraft structure, a secondary aircraft structure and a control surface positionable relative to said primary and secondary aircraft structures, the load path between the primary and secondary aircraft structure and the control surface defining a dual load path, said actuator system, comprising:

a) an upper actuator assembly, comprising;

i. an upper actuator assembly housing;

ii. a gear assembly supported by said upper actuator assembly housing;

iii. a motor assembly operatively associated with said gear assembly;

iv. an upper primary gimbal assembly mounted to said upper actuator assembly housing, said upper primary gimbal assembly being securely connected to a primary aircraft structure; and

,

v. an upper load sensing assembly securely attached to a secondary aircraft structure;

b) a ball screw assembly operatively connected to said gear assembly, said ball screw assembly, comprising;

i. a ball screw;

ii. a ball nut assembly translatable along said ball screw; and

,

iii. a secondary inverted thread nut in an unloaded standby mode operatively positioned about said ball nut assembly;

c) a tie-rod assembly positioned within said ball screw assembly, said tie-rod assembly having an upper end securely attached to said upper load sensing assembly, wherein said upper load sensing assembly defines an upper portion of a secondary load path of a dual load path between the secondary aircraft structure and a control surface, said dual load path including a primary load path acting and reacting the applied aerodynamic load to the control surface and said secondary load path in a stand-by, unloaded mode, said upper load sensing assembly providing upper indications of the applied forces in said upper portion of said secondary load path when an upper portion of the primary load path is disconnected;

d) a lower actuator assembly, comprising;

i. a lower primary gimbal assembly operatively connected to said ball screw assembly, defining a lower portion of the primary load path;

ii. a lower secondary gimbal assembly positioned about said lower primary gimbal assembly and securely connected to the control surface;

iii. a yoke assembly operatively connected to said secondary inverted thread nut and to said lower secondary gimbal assembly; and

,

iv. a lower load sensing assembly securely attached to said yoke assembly for providing said operative connection between said yoke assembly and said lower secondary gimbal assembly, wherein,

1. a lower portion of said primary load path is defined by the load from said ball screw to said ball nut assembly to said lower primary gimbal assembly to said control surface;

2. a lower portion of said secondary load path is defined by the load from said ball screw to said secondary inverted thread nut to said yoke assembly to said lower load sensing assembly to said lower secondary gimbal assembly to said control surface; and

,

3. said lower load sensing assembly provides lower indications of the applied forces in said lower portion of said secondary load path when the lower portion of said primary load path is disconnected; and

,

e) a computer system for receiving said upper and lower indications of applied forces and analyzing said upper and lower indications, thereby monitoring the structural integrity and safety of said dual load path by annunciating the detection of a failed portion thereof.

2. The actuator system of claim 1, wherein:

a) said upper load sensing assembly, comprises a pair of upper load sensing elements;

b) said lower load sensing assembly, comprises a pair of lower load sensing elements; and

,

c) said computer system comprises;

i. a first computer channel operatively connected to a first upper sensing element of said pair of upper load sensing elements and to a first lower sensing element of said pair of lower sensing elements; and

,

ii. a second computer channel operatively connected to a second upper sensing element of said pair of upper load sensing elements and to a second lower sensing element of said pair of lower sensing elements, said first computer channel and said second computer channel being electrically and mechanically segregated.

3. The actuator system of claim 2, wherein,

a) each of said upper load sensing elements is dual channel;

and,

b) each of said lower load sensing elements is dual channel, said dual channels being electrically and mechanically segregated.

4. The actuator system of claim 1, wherein said control surface comprises a horizontal stabilizer.

5. The actuator system of claim 1, wherein said control surface comprises an aileron.

6. The actuator system of claim 1, wherein said control surface comprises a wing trailing edge flap.

7. The actuator system of claim 1, wherein said control surface comprises a wing leading edge slat.

8. The actuator system of claim 1, wherein said control surface comprises an elevator.

9. The actuator system of claim 1, wherein said control surface comprises an Elevon.

10. The actuator system of claim 1, wherein said control surface comprises a Flaperon.

11. The actuator system of claim 1, wherein said control surface comprises a wing.

12. The actuator system of claim 1, wherein said computer system powers said upper and lower load sensing assemblies.

13. An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure, the actuator being of a type including:

a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly;

b) a ball screw assembly operatively connected to the gear assembly; and

,

c) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of said control surface,

wherein said actuator load path monitoring system, comprises;

a) an upper load sensing assembly positioned in an upper load path between said upper actuator assembly and said aircraft structure, said upper load sensing assembly providing upper indications of the applied forces in said upper load path when the upper load path is disconnected;

b) a lower load sensing assembly positioned in a lower load path between said lower actuator assembly and said control surface, said lower load sensing assembly providing upper indications of the applied forces in said lower load path when the lower load path is disconnected; and

,

c) a computer system for receiving said upper and lower indications of applied forces and analyzing said upper and lower indications, thereby monitoring the structural integrity and safety of the upper and lower load paths by annunciating the detection of a failed portion thereof.

14. The actuator load path monitoring system of claim 13, wherein said upper load sensing assembly and said lower load sensing assembly each comprises a dynamometric load sensing pin having at least one strain gauge bridge positioned within the housing of the pin, each load sensing pin having external characteristics commensurate for mating engagement with mating surfaces of the upper actuator assembly and lower actuator assembly.

15. The actuator load path monitoring system of claim 13, wherein:

a) said upper load path in which said upper load sensing assembly is positioned comprises an upper portion of a secondary load path of a dual load path; and

,

b) said lower load path in which said lower load sensing assembly is positioned comprises a lower portion of said secondary load path of said dual load path.

16. The actuator load path monitoring system of claim 13, wherein:

a) said upper load path in which said upper load sensing assembly is positioned comprises an upper portion of a primary load path of a dual load path; and

,

b) said lower load path in which said lower load sensing assembly is positioned comprises a lower portion of said primary load path of said dual load path.

17. The actuator load path monitoring system of claim 13, wherein:

a) said upper load sensing assembly, comprises a pair of upper load sensing elements;

b) said lower load sensing assembly, comprises a pair of lower load sensing elements; and

,

c) said computer system comprises;

i. a first computer channel operatively connected to a first upper sensing element of said pair of upper load sensing elements and to a first lower sensing element of said pair of lower sensing elements; and

,

ii. a second computer channel operatively connected to a second upper sensing element of said pair of upper load sensing elements and to a second lower sensing element of said pair of lower sensing elements, said first computer channel and said second computer channel being electrically and mechanically segregated.

18. The actuator load path monitoring system of claim 13, wherein:

a) each of said upper load sensing elements is dual channel; and

,

b) each of said lower load sensing elements is dual channel, said dual channels being electrically and mechanically segregated.

19. The actuator load path monitoring system of claim 13, wherein each of said load sensing elements, is an environmentally and hermetically sealed element capable of operating in an aircraft environment of −

65°

C. to +85°

C.

20. The actuator load path monitoring system of claim 13, wherein said computer system powers said upper and lower load sensing assemblies.

21. A method for monitoring the load path of an actuator for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure, the actuator being of a type including:

a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly;

b) a ball screw assembly operatively connected to the gear assembly; and

,

c) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of said control surface,

wherein the method of monitoring the load path of the actuator, comprises the steps of;

a) positioning an upper load sensing assembly in an upper load path between said upper actuator assembly and said aircraft structure, said upper load sensing assembly providing upper indications of the applied forces in said upper load path when the upper load path is disconnected;

b) positioning a lower load sensing assembly in a lower load path between said lower actuator assembly and said control surface, said lower load sensing assembly providing upper indications of the applied forces in said lower load path when the lower load path is disconnected; and

,

c) utilizing a computer system for powering, monitoring and for receiving said upper and lower indications of applied forces and analyzing said upper and lower indications, thereby monitoring the structural integrity and safety of the upper and lower load paths by annunciating the detection of a failed portion thereof.

22. An actuator system for an aircraft of a type having a primary aircraft structure, a secondary aircraft structure and a control surface positionable relative to said primary and secondary aircraft structures, the load path between the primary and secondary aircraft structure and the control surface defining a dual load path, said actuator system, comprising:

a) an upper actuator assembly, comprising;

i. an upper actuator assembly housing;

ii. a gear assembly supported by said upper actuator assembly housing;

iii. a motor assembly operatively associated with said gear assembly;

iv. an upper primary gimbal assembly mounted to said upper actuator assembly housing, said upper primary gimbal assembly being securely connected to a primary aircraft structure; and

,

v. an upper load sensing assembly securely attached to a secondary aircraft structure,

b) a power screw assembly operatively connected to said gear assembly, said ball screw assembly, comprising;

i. a power screw;

ii. a nut assembly translatable along said power screw; and

,

iii. a secondary inverted thread nut in an unloaded standby mode operatively positioned about said nut assembly;

c) a tie-rod assembly positioned within said power screw assembly, said tie-rod assembly having an upper end securely attached to said upper load sensing assembly, wherein said upper load sensing assembly defines an upper portion of a secondary load path of a dual load path between the secondary aircraft structure and a control surface, said dual load path including a primary load path acting and reacting the applied aerodynamic load to the control surface and said secondary load path in a stand-by, unloaded mode, said upper load sensing assembly providing upper indications of the applied forces in said upper portion of said secondary load path when an upper portion of the primary load path is disconnected;

d) a lower actuator assembly, comprising;

i. a lower primary gimbal assembly operatively connected to said power screw assembly, defining a lower portion of the primary load path;

ii. a lower secondary gimbal assembly positioned about said lower primary gimbal assembly and securely connected to the control surface;

iii. a yoke assembly operatively connected to said secondary inverted thread nut and to said lower secondary gimbal assembly; and

,

iv. a lower load sensing assembly securely attached to said yoke assembly for providing said operative connection between said yoke assembly and said lower secondary gimbal assembly, wherein,

1. a lower portion of said primary load path is defined by the load from said power screw to said nut assembly to said lower primary gimbal assembly to said control surface;

2. a lower portion of said secondary load path is defined by the load from said power screw to said secondary inverted thread nut to said yoke assembly to said lower load sensing assembly to said lower secondary gimbal assembly to said control surface; and

,

3. said lower load sensing assembly provides lower indications of the applied forces in said lower portion of said secondary load path when the lower portion of said primary load path is disconnected; and

,

e) a computer system for receiving said upper and lower indications of applied forces and analyzing said upper and lower indications, thereby monitoring the structural integrity and safety of said dual load path by annunciating the detection of a failed portion thereof.