Mechanism for eliminating limit cycle oscillations on servocontrolled aerodynamic control surfaces

• US 20050178897A1
• Filed: 12/30/2004
• Published: 08/18/2005
• Est. Priority Date: 12/31/2003
• Status: Active Grant

• Current Assignee: Airbus Operations SL (Airbus SE)
• Original Assignee: Airbus Espana SL (Airbus SE)
• Inventors: Moreno, Alvaro Villalta
• Granted Patent: US 7,175,132 B2
• Time in Patent Office: Days
• US Class Current: 244/99.130
• CPC Class Codes: B64C 13/38 with power amplification
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/30 Balancing hinged surfaces, e.g. dynamically

Abstract

Servocontrolled aerodynamic control surfaces, such as the direction rudder (1) of an airplane, are equipped with servoactuators (5). The bearing supports (3) of the rotation axis (2) or hinged axis give rise to the formation of free play for the manufacturing tolerances, that will be more pronounced with the wear of the bearings or joint elements.

The mechanism (8) in question includes an elastic element (10) fixed to the structure (4) wherein the control surface (1) is jointed, connected rigidly to an articulated connecting rod (12) having a following roller (13) of a cam (9) integral to the control surface (1). The cam (9) profile produces a continuous nonlinear, angular deformation, of the elastic element in order to determine a force torque on the control surface (1) that is maximum in the neutral position of the control surface and manages to be eliminated in the extreme side deviations.

Claims

1. Mechanism for eliminating limit cycle oscillations on servocontrolled aerodynamic control surfaces, these surfaces being equipped with servoactuators and whose supports of the rotation axis or the hinged axis, determine free play between the manufacturing tolerances and the wear of the bearings or joint elements, wherein it includes an elastic element, spring or torsion bar, fixed to the structure wherein the control surface is jointed, to which an articulated rod is rigidly connected, said articulated rod provided in its ends with a following roller of a cam integral to the control surface and with a profile that produces continuous nonlinear deformation, of the elastic element defining a force torque on the control surface, that reduces when the deviations of the control surface increase, being “

0”

for positive and negative deviations that exceed a pre-established angular value.