Patent Application
20090091476
The present invention provides a sensing arrangement to positively determine the locked or locked status of an internally locking actuator. The present invention provides a lock sensor mechanism that may be used in an internally locking actuator used in aircraft landing gear.
An actuator is a mechanism that causes a device to be adjusted or moved, or turned on or off. Hydraulic actuators are used in aircraft landing gear to extend and retract the landing gear. In general, each actuator includes a cylinder or pressure vessel that contains a piston. The piston extends and retracts through the addition of a working fluid (hydraulic oil or compressed gas). Often it is desirable to add a mechanical lock facility to the actuator such that the piston may be mechanically restrained in either of or both the fully extended position and the fully retracted position. A variety of methods are known in the art to provide the mechanical locking facility—a lock which remains set in the absence of the working fluid. These include, but are not limited to the collet lock and the segment lock. In most mechanical lock mechanisms, a separate, independently movable piston within the primary piston is employed to perform the lock and unlock function. This lock piston is typically designed such that when the primary piston is not at either end of its displacement, the working fluid preferentially acts on the primary piston to move it. When the primary piston reaches the end of its displacement, the working fluid then works to displace the lock piston. In the case of the segment lock, the lock piston moves a plurality of lock segments that are sized to fit in grooves located in the cylinder when the lock segments are radially aligned with the grooves. The lock piston is unable to displace fully unless the lock segments mate with the grooves in the cylinder to achieve a true lock.
Knowing that the actuator has achieved a true lock is imperative in aircraft landing gear applications where this lock is used to ensure that the landing gear do not fold upon landing. A sensing system is employed to indicate to the pilot and the flight control system of the aircraft that a true, mechanical lock has been achieved. The lock piston, by virtue of being constrained within the primary piston is by design difficult to sense. The location of the lock piston must be somehow communicated outside of the piston and cylinder. This is performed by connecting to the lock piston a pin, which slides through a slot in the primary piston. This pin is generally used to align with and connect to a lock sensing mechanism to indicate whether the actuator is locked or unlocked. When the lock segments are not located within the external grooves the lock piston is unable to move past the lock segments and the lock indicator pin will not align with or connect to the lock sensing mechanism. When the lock segments are located within the external grooves the internal pressure in the vessel moves the lock piston beyond the lock segments and the lock indicator pin is able to align with and connect to the lock sensing mechanism.
Most of the current lock sensing mechanisms that are used in aircraft actuators are mechanical locking devices. As an example, in one device the sensing mechanism is located in an indicator housing assembly which is located at the end of the actuator side brace. A switch lever, located in the lock sensing mechanism extends from the indicator housing assembly into the path of the lock mechanism of the actuator piston. The lock sensing mechanism is activated when a lock indicator pin, connected to the locking mechanism in the piston, moves the switch lever magnifying a displacement on the other end of the lever. This magnified distance moves a target guide, which moves a target into proximity sensor range. The proximity sensors transmit a signal indicating that the piston is fully extended and locked.
The lock sensing mechanisms that include several mechanical parts may be worn down over time. Additionally, mechanical parts can fail to due to interference from foreign bodies or from general mechanical fatigue. It is therefore preferable to use a sensor that does not include mechanical parts and therefore may reduce the necessity for replacement or maintenance of the parts.
The present invention provides an internal lock sensor, for use in an actuator having an internal piston connected to a lock indicator ring and having at least one lock segment connected thereto, the lock sensor comprising at least one field emitting device connected to the actuator and operable to emit a field and to measure a change in the emitted field and at least one target connected to the internal piston and operable to move into and out of the field emitted by the at least one field emitting device, the at least one target being operable to change the emitted field when located in the field. The at least one field emitting device may be a proximity sensor. The at least one target may be made from metallic material. The at least one target may be, for example, ferromagnetic.
The present invention further provides an internal lock sensor where the target is integral with the lock indicator ring, for example the target may be the lock indicator ring or may be mounted on the lock indicator ring.
The present invention further provides a sensor including a second field emitting device located longitudinally from a first field emitting device at a location at which the field emitted from the second field emitting device is spaced from the field emitted from the first field emitting device, the at least one target being operable to move within each emitted field.
The present invention further provides a sensor including a second field emitting device located in the same plane as a first field emitting device and circumferentially located relative to the first field emitting device to space the field emitted from the first field emitting device from the second field emitting device.
The present invention further provides an aircraft landing gear actuator comprising a lock sensor described herein. The present invention further provides an actuator comprising a lock sensor described herein.
The present invention further provides an internal lock sensor, for use in an actuator the lock sensor comprising at least one field emitting device connected to the actuator and operable to emit a field and to measure a change in the emitted field and at least one target connected to actuator and operable to move into and out of the field emitted by the at least one field emitting device, the at least one target being operable to change the emitted field when located in the field. The at least one field emitting device may be a proximity sensor. The at least one target may be made from metallic material. The at least one target may be, for example, ferromagnetic.
The present invention further provides an internal lock sensor where the target is integral with the lock indicator ring, for example the target may be the lock indicator ring or may be mounted on the lock indicator ring.
The present invention further provides a method for indicating the status of a lock sensor in an actuator, the lock sensor having at least one field emitting device and a target operable to move into and out of the field emitted from the field emitting device, the method comprising the steps of (i)emitting a field from the at least one field emitting device (ii)measuring the emitted field and(iii) reporting any change in the emitted field.
The present invention further provides a sensor that includes at least one positioning device for positioning the at least one field emitting device relative to the internal piston. The positioning device may be a washer or a shim. Additionally the at least one positioning device may be integral with the field emitting device and may comprise a washer and flange arrangement or a threading arrangement for altering the position of the field emitting device relative to the internal components of the actuator.
The present invention will now be described in further detail with reference to the accompanying drawings in which:
Before discussing the lock sensor of the present invention in detail, reference will now be made to
The present invention will now be described in further detail with reference to
The lock sensor of the present invention will now be described in further detail with reference to
As an example, the field emitting device 46 may be a proximity sensor, such devices are known and commercially available, for example proximity sensors manufactured by Eldec Corporation. Examples of proximity sensors that may be used in the present invention include, but are not limited to, capacitive, eddy current killed oscillation, inductive, photoelectric, and ultrasonic. In a capacitive proximity sensor the field emitting device would act as one capacitor, and the target will include a conductive surface which will act as the second capacitor. The capacitance will vary inversely with the distance between the two capacitors and a pre-set value can be programmed to trigger target detection. In an eddy current killed oscillation proximity sensor an oscillating magnetic field is emitted by the sensor. In the presence of electrically conductive materials (such as a target) electrical eddy currents are generated. The sensor is designed such that the energy induced in the conductive target is sufficient to halt the oscillation of the magnetic field—killing the oscillation. In such a system the target may be made of metal and when moved into proximity with the field emitting device will cease oscillating thereby indicating a breach of the field. Other proximity sensors include photoelectric devices and ultrasonic proximity sensors.
In one embodiment, the at least one field emitting device 46 is mounted on the rod end cap 50 of the side brace 52 of the actuator. The at least one field emitting device 46 may be mounted using threads, i.e a screw-type fit. It will be understood that the field emitting device 46 may be mounted by any means known to a person skilled in the art, in a manner that provides a pressure seal. Examples of ways for mounting or attaching the field emitting device 46 to the rod end cap, include but are not limited to, threading the field emitting device into the rod end cap, mounting the field emitting device to the rod end cap using an oaring and a flange that may be attached to the rod end cap using, for example, bolts or screws, for which examples are illustrated in
In the embodiment illustrated in
The position for the mounting of the target 48 is chosen so that in the unlocked position the target 48 is not located within the field emitted by the field emitting device 46 and is located at a position outside of the field emitting device 46 sensing range. When the actuator 20 is in the locked position the target 48 moves within the field, either completely or partially so that the field is interrupted and the field emitting device 46 can identify that the field has been interrogated.
In an alternative embodiment the target 48 may be mounted directly on the lock piston 28. In this arrangement the mounting of the target 48 to the lock piston 28 may replace the lock indicator ring. The target 48 will be mounted on the lock piston 28 at a location that is operable to move into and out of the field. It will be understood that the position of the target 48 in this embodiment will be chosen in order to fulfill the requirements of the disclosed invention.
Due to production tolerances of the components in the actuator, it is preferable to provide axial adjustment of the field emitting device 46 in order to calibrate (rig) the field emitting device 46 for standard operation. The ability to provide axial adjustment allows field interchangeability of the actuator unit. In the embodiments described herein, this adjustment can be made at the attachment point of the field emitting device 46 to the end cap of the side brace. For example, if the field emitting device 46 is threaded onto the side brace then the axial adjustment may be made by releasing the threading attachment of the device 46 to the end cap, i.e. unscrewing the field emitting device or screwing the field emitting device to change the radial location of the field relative to the internal components of the actuator. In addition, washers and/or shims may be included in the attachment of the field emitting device in order to change the radial position thereof.
The field emitting device 46 of the present invention will be chosen in order that it can withstand the pressure requirements of the actuator. In particular, the attachment of the field emitting device 46 must provide a pressure seal at the point of attachment to the end cap of the side brace.
When the lock sensor of the present invention is used in an actuator located in an aircraft landing gear application preferably the lock sensor includes two or more field emitting devices 46. The inclusion of an additional field emitting device 46 provides a back up to the system in case of failure of one of the field emitting devices 46. In the landing gear application it is preferable to have a back up to ensure that a measurement is taken to indicate to the pilot of the aircraft whether the actuator system is in the locked or unlocked position.
In an alternative embodiment of the present invention the lock sensor 44 may include two or more field emitting devices 46 located within the same circumferential plane. When the target 48, i.e. the lock indicator ring, moves into the plane in which the field emitting devices 46 are located then each field emitting device 46 identifies the presence of the target 48 and more than one indication of the actuator being in the locked position is made. This embodiment provides one example of a system that includes a back up measurement. An alternative embodiment in which two field emitting devices 46 are included may position a second field emitting device 46 longitudinally spaced along the axis of the actuator from the first field emitting device 46. In this embodiment the two field emitting devices 46 may be positioned so that when the actuator is in the locked position the target 48 is located within the field of the first field emitting devices 46. When the actuator is in the unlocked position the target 48 will be located within the field of the second field emitting device 48.
In an alternative embodiment the at least one field emitting device 48 is located adjacent the lock segments 26 and the at least one target 48 is integral with or attached to one or more of the lock segments 26. In this embodiment the field emitted by the at least one field emitting device 46 extends a predetermined distance radially inwards from the periphery of the actuator. The field emitting devices 46 in this embodiment will be designed so that the field emitted does not radially extend within reach of being breached by the lock segment 26 containing the target 48 when they are in the unlocked position. This means that when the lock segments 26 are not located in the grooves of the piston they do not breach the field emitted by the at least one field emitting device 46. However, when the lock segments 26 are located in the grooves in the locked position the field is breached and an indication that the actuator is locked is made.
It will be understood that the field emitting device 46 may be operable to only record a change in the field emitted therefrom. Alternatively, the field emitting device 46 may be capable of analysing the recorded change or transmitting the recorded change to a control system located on or near the actuator so that the reporting of or manipulation of the reading is performed by the control system. Any recorded change in the field will be used to send an indication to the pilot, when used in aircraft landing gear, to indicate that the system is in the locked or unlocked position.
The use of the inductance proximity sensor will now be discussed with reference to
While this invention has been described with reference to illustrative embodiments and examples, the description is not intended to be construed in a limiting sense. Thus, various modifications of the illustrative embodiments, as well as other embodiments of the invention, will be apparent to persons skilled in the art upon reference to this description. It is therefore contemplated that the appended claims will cover any such modifications or embodiments. Further, all of the claims are hereby incorporated by reference into the description of the preferred embodiments.
All publications, patents and patent applications referred to herein are incorporated by reference in their entirety to the same extent as if each individual publication, patent or patent application was specifically and individually indicated to be incorporated by reference in its entirety.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2,479,454 | Aug 2004 | CA | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/CA2005/001303 | 8/30/2005 | WO | 00 | 7/28/2008 |
