Locking sleeve for an actuator

Abstract

The present invention relates to a device for locking an actuator, preferably a locking sleeve, with two half-shells that can pivot relative to each other between an open position and a locked position, configured such that, in the locked position, the two half-shells rest on their end faces turned towards each other. The device does not have a bayonet closure, but a tongue-and-groove joint.

Description

Title of the invention: Locking sleeve for an actuator

[0001] The present invention relates to a locking device, preferably a locking sleeve, for a linear control valve, for example an actuator.

[0002] In the event of failure of an actuator, for example of a spoiler actuator, during a flight, the flight cannot continue safely if the actuator is not blocked or immobilized.

[0003] In this context, the present invention aims to mitigate, or even completely eliminate, the problems associated with the prior art. In particular, the present invention aims to provide a device for blocking or immobilizing an actuator, for example an aircraft spoiler actuator, in order to allow flight to continue in the event of actuator failure until conditions favorable to repairing the actuator are met.

[0004] This task is performed by a device and a system described in the independent claims. Advantageous improvements of the invention are the subject of dependent claims.

[0005] According to these, a device is provided for locking an actuator, preferably a locking sleeve, comprising two half-shells that can pivot relative to each other between an open position and a locking position, which are configured such that, in the locking position, the two half-shells are supported on their end faces turned towards each other.

[0006] The two half-shells are preferably connected to each other at one end by a hinge. At the end opposite the hinge, the half-shells are also preferably supported in the locked position.

[0007] Unlike conventional solutions with a bayonet closure, the two half-shells thus preferably form a hollow cylinder closed in the locked position. They also allow for complete engagement of the thread between the device and an actuator housing.

[0008] Unlike conventional solutions, the solution according to the invention does not include a bayonet closure, but preferably a tongue and groove connection.

[0009] The device may include at least one fastening element for fixing the half-shells to each other in the locked position, the fastening element preferably being in the form of at least one screw which passes through a part of one of the half-shells and can be screwed into a part of the other half-shell.

[0010] According to one embodiment, the fastening element may include at least two screws which are configured to hold the two half-shells in contact with their end faces turned towards each other.

[0011] In addition, the device may include, at least at one longitudinal end, a thread that is configured to engage with another component, preferably an actuator, in order to hold the device preferably removably on the component.

[0012] In addition, the device may include an anti-rotation device which includes at least one pre-stressed lock which is configured to engage in a corresponding recess of a housing in order to prevent rotation of the device relative to the housing.

[0013] At least one lock can be made in the form of a spring-loaded pre-stressed ball, which is configured to engage in a corresponding groove in the housing.

[0014] The anti-rotation device may further include at least one bushing in which the ball is guided, the bushing being configured to allow movement of the ball in the direction of the spring force and in the opposite direction.

[0015] Another aspect of the invention relates to a linear control valve, preferably an actuator, with a housing, the housing having a thread which is configured to engage in a corresponding thread of a device according to the present invention.

[0016] The housing of the regulating valve may be provided, on a front face configured to bear against the device according to the present invention, with at least one, preferably several radially extending grooves. A ball of an anti-rotation device of the device may enter the grooves and / or cross them.

[0017] Another aspect of the invention relates to a system comprising a linear actuator according to the present invention and a device according to the present invention, the device being removably engaged with the housing of the control valve by means of a threaded engagement at one of its longitudinal ends and, preferably, at least one lock or ball of the anti-rotation device of the device being engaged with a groove of the housing.

[0018] Another aspect of the invention relates to the use of a device according to the present invention and / or a system according to the present invention for the manufacture and / or equipping of an aircraft, in particular an airplane.

[0019] The invention further includes an aircraft, in particular an airplane, with at least one device according to the present invention and / or a system according to the present invention.

[0020] Another aspect of the present invention relates to a method of manufacturing and / or equipping an aircraft, in particular an airplane, comprising the step of placing at least one device according to the present invention and / or a system according to the present invention on the aircraft, preferably on an actuator thereof.

[0021] It should be noted at this stage that all features disclosed in the context of a particular embodiment in this application are also included in any other combination or in isolation from the disclosure, although An explicit disclosure has been omitted here to avoid redundancy. All the features of the invention described herein may therefore be combined with each other or claimed individually.

[0022] Other information and advantages of the invention are detailed with the aid of an example embodiment shown in the drawing. Illustrations: [Fig.1]: View of an actuator with a locking sleeve according to the invention, [Fig.2]: Detailed view of a part of the [Fig.1], [Fig. 3]: Cross-sectional view of a safety mechanism of the locking sleeve of [Fig. 1] and [Fig.4]: Perspective view of the locking sleeve of [Fig.1] in the open position.

[0023] Figure 1 shows a linear control valve 1, for example a hydraulic cylinder, with a fixed eyelet 2 and a linearly movable eyelet 3. A device 4 according to an embodiment of the invention is shown, which, by complementary shape, locks the position of the movable eyelet 3 relative to the fixed eyelet 2 in both directions of movement. The locking is achieved by the fact that the device 4 is connected to the housing 6 by means of the thread 5 and to the eyelet 3 by means of the ribs 7a and 7b.

[0024] In other words, the device may include housings for ribs of the linear actuator, in particular an eyelet thereof, in order to retain the device on the regulating valve. Preferably, each half-shell includes at least one such housing.

[0025] [Fig.2] shows a detailed view of the circled area of ​​[Fig.1].

[0026] The assembly of device 4 is guaranteed by the fact that it consists of two half- shells 8a and 8b, as illustrated for example in [Fig.4]. To facilitate the handling of device 4, the two half-shells 8a and 8b are connected by a hinge 9.

[0027] In the open state, as shown in [Fig.4], one of the two half-shells 8a or 8b can be placed around the rib 7a or 7b of the movable eyelet 3. It is necessary to ensure beforehand that the distance between the movable eyelet 3 and the fixed eyelet 2 is sufficient to prevent the thread 5 of the device 4 from colliding with the housing 6 during this operation.

[0028] By then closing the device 4, the second half-shell 8a or 8b also wraps around the rib 7a or 7b.

[0029] Tightening the two screws 10 prevents the device 4 from opening. By then rotating the device 4 around the axis of the thread 5 and simultaneously bringing the movable eyelet 3 closer to the fixed eyelet 2, the thread 5 is fully engaged and the eyelets 2 and 3 are thus locked relative to each other.

[0030] The design of the device 4 shown in the figures allows manual rotation thanks to a non-slip surface 11.

[0031] An unintentional disengagement of the threaded connection 5, for example under the effect of vibrations, is prevented by the anti-rotation device 12 shown in [Fig.3].

[0032] The housing 6 is provided with several radial grooves 13 on its front face. The device 4 includes a ball 14 which is actuated by a spring 15.

[0033] The sleeve 16 prevents the loss of the ball thanks to a slightly smaller drilling diameter at the end of the drilling 17 and allows the ball 14 to move against the force of the spring.

[0034] During the screwing of the thread 5, the ball 14 comes into contact with the front face of the housing 6.

[0035] As the screwing continues, the ball 14 sinks into the device 4 against the force of the spring, because the device 4 continues to move closer to the fixed eyelet 2, however, the ball 14 can no longer follow this movement due to its contact with the front face of the housing 6.

[0036] As screwing continues, the ball 14 reaches one of the grooves 13, which results in it being pushed into the groove under the effect of the spring force.

[0037] The grooves 13 are geometrically configured such that increasing the screwing torque causes the ball 14 to come out of the groove 13.

[0038] If the operator continues to screw, the ball 14 moves in and out of the grooves 13 until the bushing 16 touches the front face of the housing 6. The assembly of the device 4 is thus completed.

[0039] In this state (sleeve 16 in contact with the front face of the housing 6), the desired prevention of loosening of the thread 5 is very probably not yet ensured, because the ball 14 is very probably not in one of the grooves 13.

[0040] However, this is only true until the ball 14 reaches the nearest groove 13 as a result of an unintentional loosening of the thread 5. The sinking of the ball 14 into this groove 13 then prevents any further loosening.

[0041] In order to guarantee the dismantling of the device 4, the grooves 13 are also geometrically configured in such a way that the possibility described above of continuing to rotate during the engagement of the anti-rotation device by increasing the torque, even in the direction of loosening, also exists.

Claims

Demands

1. Device (4) for locking an actuator (1), preferably a locking sleeve, with two half-shells (8a, 8b) that can pivot relative to each other between an open position and a locking position, which are configured such that, in the locking position, the two half-shells (8a, 8b) are supported on their end faces turned towards each other.

2. Device (4) according to claim 1, characterized in that the device (4) does not have a bayonet closure, but a groove and tongue connection.

3. Device (4) according to claim 1 or 2, characterized in that the device (4) comprises at least one fastening element (10) by means of which the half-shells (8a, 8b) can be fixed to each other in the locking position, the fastening element (10) preferably being in the form of at least one screw which passes through a part of one of the half-shells (8a, 8b) and can be screwed into a part of the other half-shell (8a, 8b).

4. Device (4) according to claim 3, wherein the fastening element (10) comprises at least two screws which are configured to hold the two half-shells (8a, 8b) in contact with their end faces turned towards each other.

5. Device (4) according to any one of the preceding claims, characterized in that the device (4) comprises, at least at one longitudinal end, a thread (5) which is configured to engage with another component, preferably an actuator (1), in order to hold the device (4) preferably removably on the component (1).

6. Device (4) according to any one of the preceding claims, characterized in that the device (4) further comprises an anti-rotation device (12) which includes at least one pre-stressed lock which is configured to engage in a corresponding recess of a housing (6) in order to prevent rotation of the device (4) relative to the housing (6).

7. Device (4) according to claim 6, characterized in that at least one latch is configured in the form of a spring-loaded ball (14) (15) which is configured to engage in a corresponding groove (13) of the housing (6).

8. Device (4) according to claim 7, characterized in that the anti-rotation device (12) further comprises a sleeve (16) in which the ball (14) is guided, the sleeve (16) being configured to allow movement of the ball (14) in the direction of the force of the spring (15) and in the opposite direction.

9. Linear control valve (1), preferably an actuator, comprising a housing (6), the housing (6) having a thread that is configured to engage in a corresponding thread (5) of a device (4) according to any one of the preceding claims.

10. Linear control valve (1) according to claim 9, characterized in that the housing (6) is provided, on a front face which is configured to bear against a device (1) according to any one of claims 1 to 8, with at least one, preferably several radially extending grooves (13).

11. System comprising a linear control valve (1) according to any one of claims 9 and 10 and a device (4) according to any one of claims 1 to 8, the device (4) being removably engaged with the housing (6) of the control valve (1) by means of a threaded engagement at one of its longitudinal ends and, preferably, at least one latch or ball (14) of the anti-rotation device (12) being engaged with a groove (13) of the housing (6).

12. Use of a device (4) according to any one of claims 1 to 8 and / or a system according to any one of claims 9 to 11 for the manufacture and / or equipping of an aircraft, in particular an airplane.

13. Aircraft, in particular airplane, comprising at least one device (4) according to any one of claims 1 to 8 and / or a system according to any one of claims 9 to 11.

14. A method for manufacturing and / or equipping an aircraft, in particular an airplane, comprising the step of: Placing at least one locking sleeve (4) according to any one of claims 1 to 8 and / or a system according to any one of claims 9 to 11 on the aircraft, preferably on an actuator (1) of the aircraft.

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