Search

BR-102021002172-B1 - Landing Gear System, Retraction Methods and Landing Gear System Installation

BR102021002172B1BR 102021002172 B1BR102021002172 B1BR 102021002172B1BR-102021002172-B1

Abstract

LANDING GEAR SYSTEM, RETRACTION AND DEPLOYMENT METHODS OF A LANDING GEAR SYSTEM. A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss structure articulated to an aircraft structure and configured to rotate about an axis; a retraction actuator configured to rotate the truss structure about the axis; a first truss link articulated to the truss structure; a second truss link articulated to the first truss link; a truss locking link articulated to the truss structure and to the second truss link; and a linkage actuator configured to rotate the first truss link relative to the truss structure.

Inventors

  • James Acks

Assignees

  • GOODRICH CORPORATION

Dates

Publication Date
20260317
Application Date
20210205
Priority Date
20200206

Claims (15)

  1. 1. Landing gear system (100) for an aircraft, characterized in that it comprises: a truss structure (102) articulatedly connected to an aircraft structure and configured to rotate about an axis; a retraction actuator (104) configured to rotate the truss structure (102) about the axis; a first truss link (106) articulatedly connected to the truss structure (102); a second truss link (110) articulatedly connected to the first truss link (106), wherein the first truss link (106) has a first end articulated to the truss structure (102) on a first rotating axis (108) and a second end connected to the second truss link (110) on a second rotating axis (112); a truss locking link (116) articulated to the truss structure (102) and to the second truss link (110); a linkage actuator (128) configured to rotate the first truss link (106) with respect to the truss structure (102); and a lever (118) articulatedly connected to the first truss link (106) and to the second truss link (110) on the second rotating axis (112).
  2. 2. Landing gear system according to claim 1, characterized in that it further comprises a shock absorber (126) articulatedly connected to the first truss link (106) and to the lever (118).
  3. 3. Landing gear system according to claim 2, characterized in that it further comprises an axle fixing member (120) articulatedly connected to the lever (118).
  4. 4. Landing gear system according to claim 3, characterized in that it further comprises a ground articulation link (134) articulated to the axle fixing member (120).
  5. 5. Landing gear system according to claim 4, characterized in that it further comprises a retraction link (132) articulated to the truss locking link (116) and to the ground articulation link (134).
  6. 6. Landing gear system according to claim 5, characterized in that it further comprises a spacer link (138) connecting the ground articulation link (134) and the retraction articulation link (132) to the first truss link (106).
  7. 7. Landing gear system according to any one of claims 1 to 6, characterized in that the second truss link (110) is a first-side or left-side second truss link having a first end articulated to the first truss link (106) and a second end articulated to a second-side or right-side second truss link.
  8. 8. Landing gear system according to claim 7, characterized in that the first truss link (106) is a first side or left side truss link (106) and the articulation actuator (128) is configured to rotate the first side or left side truss link (106) relative to the truss structure (102) and a first side or right side truss link relative to the truss structure (102).
  9. 9. Landing gear system according to claim 8, characterized in that it further comprises a ground articulation link articulated to an axle fixing member (120), and that it further comprises a retraction articulation link (132) articulated to the truss locking link (116) and to the ground articulation link (134).
  10. 10. Landing gear system according to claim 1, characterized in that a spacer link (138) connects a ground-bound articulation link (134) and a retraction articulation link (132) to the first truss link (106) and to the second truss link (110) on the second rotating axis.
  11. 11. Landing gear system according to claim 10, characterized in that the ground articulation link (134) is articulated to an axle fixing member (120) and the retraction articulation link (132) is articulated to the truss locking link (116).
  12. 12. Method for retracting a landing gear system (100) for an aircraft as defined in claim 1 with that truss structure (102) articulatedly connected to an aircraft structure, characterized in that the method comprises: rotating a first truss link (106) with respect to the truss structure (102) to bring a wheel coupled to the first truss link (106) towards a centerline of the aircraft; and rotating the truss structure (102) around an axis that lies perpendicular to the centerline to raise the wheel into a landing gear compartment.
  13. 13. Method according to claim 12, characterized in that a first actuator is configured to rotate the first truss link (106) with respect to the truss structure (102) and, optionally, in that a second actuator is configured to rotate the truss structure (102) around the axis.
  14. 14. Method for deploying a landing gear system (100) for an aircraft as defined in claim 1 with that truss structure (102) articulatedly connected to that aircraft structure, characterized in that the method comprises: rotating the truss structure (102) around said axis perpendicular to a centerline of the aircraft to lower a wheel coupled to a first truss link (106) articulatedly connected to the truss structure (102) from a landing gear compartment; and rotating the first truss link (106) relative to the truss structure (102) to move the wheel coupled to the first truss link (106) away from the centerline of the aircraft.
  15. 15. Method according to claim 14, characterized in that a first actuator is configured to rotate the first truss link (106) with respect to the truss structure (102) and, optionally, in that a second actuator is configured to rotate the truss structure (102) around the axis.

Description

FIELD OF THE INVENTION [001] This disclosure refers generally to aircraft landing gear and, more particularly, to articulated truss configurations adapted to minimize lateral tire wear and to rotate the landing gear in a landing gear compartment by retraction. FUNDAMENTALS OF THE INVENTION [002] Landing gear for small aircraft, such as helicopters, is often designed to remain in a fixed or landing configuration during flight. The laterally articulated landing gear was developed for helicopters, and those skilled in the art appreciate the need to eliminate or at least minimize lateral tire wear on helicopter landing gear. Often, the size and capacity of the landing gear compartment of small aircraft or helicopters are limited by features such as the fuselage structure, the location of the pilot's cabin, the size of the crew cabin, and the location of any hydraulic or electronic compartments. Consequently, the volume of space available often dictates the type of kinematic mechanism that is used to articulate the landing gear from a retracted or stowed position to an extended or deployed position. SUMMARY [003] A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss structure articulated to an aircraft structure and configured to rotate about an axis; a retraction actuator configured to rotate the truss structure about the axis; a first truss link articulated to the truss structure; a second truss link articulated to the first truss link; a truss locking link articulated to the truss structure and to the second truss link; and a linkage actuator configured to rotate the first truss link relative to the truss structure. [004] In several embodiments, the first truss link has a first end articulated to the truss structure on a first rotating axis and a second end connected to the second truss link on a second rotating axis. In several embodiments, a lever is articulated to the first truss link and to the second truss link on the second rotating axis. In several embodiments, a damper is articulated to the first truss link and to the lever. In several embodiments, an axis fastening element is articulated to the lever. In several embodiments, a ground-to-ground articulation link is articulated to the axis fastening member. In several embodiments, a retraction articulation link is articulated to the truss locking link and to the ground-to-ground articulation link. In several embodiments, a spacer link connects the ground-to-ground articulation link and the retraction articulation link to the first truss link. [005] In several embodiments, the second truss link is a second truss link on the left side, having a first end articulated to the first truss link and a second end articulated to a second truss link on the right side. In several embodiments, the first truss link is a first truss link on the left side and the articulation actuator is configured to rotate the first truss link on the left side relative to the truss structure and a first truss link on the right side relative to the truss structure. In several embodiments, a ground-related articulation link is articulated to a shaft fixing member. In several embodiments, a retraction articulation link is articulated to the truss locking link and to the ground-related articulation link. [006] In several embodiments, the first truss link has a first end articulated to the truss structure on a first rotating axis and a second end connected to the second articulation link on a second rotating axis, and a spacer link connects a ground-bound articulation link and a retraction articulation link to the first truss link and to the second truss link on the second rotating axis. In several embodiments, the ground-bound articulation link is articulated to a shaft fastening element and the retraction articulation link is articulated to the truss locking link. [007] A method is disclosed for retracting a landing gear system for an aircraft, having a truss structure articulated to an aircraft structure. In several embodiments, the method includes rotating a first truss link relative to the truss structure to bring a wheel coupled to the first truss link toward an aircraft centerline; and rotating the truss structure about an axis perpendicular to the centerline to raise the wheel into a landing gear compartment. In several embodiments, a first actuator is configured to rotate the first truss link relative to the truss structure. In several embodiments, a second actuator is configured to rotate the truss structure about the axis. [008] A method is disclosed for deploying a landing gear system for an aircraft, having a truss structure articulated to an aircraft structure. In several embodiments, the method includes rotating the truss structure about an axis perpendicular to an aircraft centerline to lower a wheel coupled to a first truss link articulated to the truss structure from a landing gear compartment; and rotating the first tru