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BR-102019026542-B1 - SYSTEM FOR DETECTING AND CONTROLLING THE POSITION OF AIRCRAFT WING SPOILERS

BR102019026542B1BR 102019026542 B1BR102019026542 B1BR 102019026542B1BR-102019026542-B1

Abstract

A system for detecting and controlling the position of a spoiler (80) of an aircraft wing is described in this document comprising: a hydraulic actuator (40) having a piston rod (43) operatively connected to the spoiler (80), the piston rod (43) being movable between a retracted position, a neutral position and an extended position; and means for supplying power to said hydraulic actuator (40); and a mechanical device (50) for detecting whether the piston rod (43) is in the retracted position, the neutral position or the extended position; and means (60), operatively connected to the mechanical device (50), which is configured to provide a change in the load applied to said hydraulic actuator (43), wherein said means (60) is configured to change said load based on whether said piston rod (43) is detected as being in said retracted position or said extended position.

Inventors

  • Raphael Medina

Assignees

  • GOODRICH ACTUATION SYSTEMS SAS

Dates

Publication Date
20260317
Application Date
20191213
Priority Date
20190614

Claims (6)

  1. 1. System for detecting and controlling the position of an aircraft wing spoiler (80) in the event of an electrical failure, comprising a system comprising: a spoiler (80); a hydraulic actuator (40) having a piston rod (43) operatively connected to the spoiler (80), the piston rod (43) being movable between a retracted position, a neutral position and an extended position; and means for supplying power to the hydraulic actuator (40); and a mechanical device (50) operatively connected to the hydraulic actuator (40) for detecting whether the piston rod (43) is in the retracted position, the neutral position or the extended position; a pressure relief valve (60), operatively connected to the mechanical device (50), which is configured to provide a change in the load applied to the hydraulic actuator (40), wherein the pressure relief valve (60) is movable between a first position (60Y) and a second position (60X) changing the load based on whether the piston rod (43) is detected by the mechanical device (50) as being in the retracted or extended position, characterized in that: the actuator (40) comprises a pressure element (44) operatively connected to the piston rod (43) through a tracking portion, the tracking portion comprising a linearly spaced first portion (47) and a second portion (46), the first and second portions having an inclined portion (45) positioned between them, such that the tracking portion comprises a variable diameter along its length, wherein, when the piston rod (43) is in the extended position, the mechanical device (50) is in contact with the first portion (47) of the tracking portion and, as the piston rod (43) retracts, the tracking portion is configured to move linearly relative to the mechanical device (50), so that when the piston rod (43) is in the retracted position, the mechanical device (50) is in contact with the second portion (46) of the hydraulic actuator (40), wherein the difference in diameter of the first and second portions results in an altered position of the mechanical device (50), thus moving the pressure relief valve (60) from the first position (60Y) to the second position (60X).
  2. 2. System according to claim 1, characterized in that, when the rod (43) is in the retracted position and the pressure relief valve (60) is in the second position (60X), upon loss of energy, the pressure relief valve (60) limits the load applied to the piston rod (43).
  3. 3. System according to claim 1 or 2, characterized in that it further comprises an anti-extension valve (30) operatively connected to the hydraulic actuator (40) and configured to prevent the piston rod (43) from moving to the extended position after loss of power.
  4. 4. System according to claim 3, characterized in that the hydraulic actuator (40) comprises a retraction chamber (41) and an extension chamber (42), and in which if the hydraulic pressure in the retraction chamber (41) is greater than the pressure in the extension chamber (42), the piston rod (43) will move to the retracted position; if the pressure in the extension chamber (42) is greater than the pressure in the retraction chamber (41), the piston rod (43) will move to the extended position and in which, with the loss of energy, the anti-extension valve (30) is movable from a first position (30Y) to a second position (30X) upon loss of energy, and in which, in the second position (30X), the piston rod (43) is prevented from moving to the extended position unless a threshold pressure is reached in the extension chamber (42).
  5. 5. System according to any one of claims 1 to 4, characterized in that the energy comprises electrical energy.
  6. 6. System according to any one of claims 1 to 4, characterized in that the energy comprises hydraulic energy.

Description

FUNDAMENTALS OF THE INVENTION [001] Wing flaps can be used on an aircraft wing to control wing lift and can be used similarly to control the aircraft's speed. When the aircraft is cruising, the wing flap lies flat along the wing. To reduce the aircraft's speed or increase lift, the flap is lowered relative to the wing. A spoiler can be actuated by a hydraulic actuator and is a movable surface mounted on an aircraft wing behind the wing flap. To control the aircraft's speed and/or roll, the spoiler can also be lifted. [002] Most aircraft have a spoiler that operates using a positive movement of an actuator rod, i.e., to extend the rod in order to support the spoiler. The actuator stroke is between a "zero" position in the housing and an extended position, and the control system is tilted to return the rod to the zero position. [003] In this way, a spoiler is normally used only in extension, and a mechanical stop inside the compartment prevents the piston rod from activating the spoiler in the zero position. [004] More recently, some aircraft have incorporated a "tilt" function in the spoiler, which uses a negative piston rod stroke - that is, returning to the housing beyond the zero position or, put another way, a stroke that moves from the zero position in the opposite direction to the direction moved in the positive stroke to extend the rod. [005] The pitch function is used to lower the spoiler relative to the wing, for example, for high-lift maneuvers. Additionally, due to the relative movement between the flap and the wing, an air gap can open between the wing and the flap. Therefore, the pitch function can also be used to negatively actuate the spoiler, creating a large air gap between the wing flap and the spoiler if the wing flap is extended. SUMMARY OF THE INVENTION [006] A system is described herein for detecting and controlling the position of an aircraft wing spoiler. The system comprises a hydraulic actuator with a piston rod that is operatively connected to the spoiler. The piston rod is movable between a retracted position, a neutral position, and an extended position. The system further comprises means for supplying power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position, or the extended position. The system further comprises means, operatively connected to the mechanical device, which are configured to provide a change in the load applied to said hydraulic actuator, wherein said means are configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position. [007] The energy supplied to the hydraulic actuator can be electrical or hydraulic. [008] In any of the examples described herein, the means configured to alter said load based on the position of said piston rod may comprise a pressure relief valve. [009] In any of the examples described herein, the pressure relief valve may be operatively connected to the mechanical device and may be configured to switch from a first position to a second position upon detection that said piston rod is in the retracted position. [0010] In any of the examples described herein, when the said piston rod is in the said retracted position and the said pressure relief valve is in the said second position, with the loss of said power, the said pressure relief valve may reduce or limit the load applied to the said piston rod. [0011] In any of the examples described herein, the system may further comprise an anti-extension valve which is operatively connected to said hydraulic actuator and configured to prevent the piston rod from moving to the extended position upon loss of said power. [0012] In any of the examples described herein, the hydraulic actuator may comprise a retraction chamber and an extension chamber, wherein if the hydraulic pressure in the retraction chamber is greater than the pressure in the extension chamber, the piston rod may move to the retracted position; and if the pressure in the extension chamber is greater than the pressure in the retraction chamber, the piston rod may move to the extended position. The anti-extension valve may be movable from a first position to a second position after loss of said power, wherein, in said second position, said piston rod may be prevented from moving to said extended position unless a threshold pressure is reached in said retraction chamber. [0013] In some examples, the threshold pressure may be 1.2 times the stall pressure of the system. BRIEF DESCRIPTION OF THE DRAWINGS [0014] Preferred examples will be described by way of example only and with reference to the drawings. [0015] Fig. 1 is a schematic view of an arrangement of the actuator control valve in an active mode, when the spoiler is in a non-overlapping position. [0016] Fig. 2 is a schematic view of an arrangement of the actuator control valve with electrical fault, when the spoiler is in a