WO2013107656A1

WO2013107656A1 - Rotation lock

Info

Publication number: WO2013107656A1
Application number: PCT/EP2013/000176
Authority: WO
Inventors: Markus Bildstein
Original assignee: Liebherr-Aerospace Lindenberg Gmbh
Priority date: 2012-01-21
Filing date: 2013-01-21
Publication date: 2013-07-25
Also published as: DE102012000987A1

Abstract

The present invention relates to a rotation lock, in particular a bidirectionally acting rotation lock, for a shaft arrangement with at least one shaft, wherein the rotation lock has at least one mechanical arrangement that is connected or can be connected to the shaft arrangement, said mechanical arrangement being formed in such a manner that it mechanically blocks the shaft in a manner that is dependent on the circular acceleration thereof and in the locking position of the rotation lock.

Description

rotation lock

The present invention relates to a rotation lock, in particular a bidirectional rotation lock, for a shaft assembly according to the preamble of claim 1, test method according to claims 15 and 16, the use of a rotation lock according to claim 18 and an aircraft according to claim 19.

Aircraft have movable flight control surfaces on their wings that are selectively extended or retracted to modify the lift-producing characteristics of the wings. This extension or retraction of the flight control surfaces and the trim of horizontal stabilizers, i. The alignment of the elevator, aileron and rudder control surfaces is known to be accomplished by a flight control actuation system.

The flight control actuating system has, inter alia, arrangements which are suitable for stopping rotational movements in a short time and subsequently for maintaining the achieved rotational position. Such arrangements are known to torque limiter and brakes in the drive train of slats and Flaps- drives and threaded spindle drives for operating trimmable horizontal stabilizers. Usually friction brakes are used for this purpose.

For aviation applications, it is necessary that the brake assemblies have the lowest possible weight. To meet this requirement, the coefficient of friction should be as high as possible. This is achieved by keeping the friction linings dry, which however proves to be particularly difficult due to the extreme environmental conditions in aircraft.

Form-locking brakes, i. Brakes, in which the rotational movement is terminated very quickly by producing a positive connection with a fixed body, have a comparatively low weight. However, the positive locking brakes have the disadvantage that the rotational energy is not converted into heat and thus degraded, but is stored in the form of elastic deformation. This disadvantage is not of great importance in flight control, since such applications are low-speed torsionally elastic systems.

When braked, the brake should have the least possible rotational play. This can not be realized with the known form-locking brakes, which are based on interlocking claws, since these brakes require a correspondingly high rotational play in order to allow the brake to engage from the rotation out.

There are known bidirectional rotation locks, which are opened by means of spring force and by means of electromagnet. In aerospace applications, actuation is usually performed by a computer. After an actuation request, first the correctness of the request is checked and after successful testing the power supply to the electromagnet is interrupted. As a result, the magnetic field in the electromagnet is degraded. Thus, spring force is available to switch the lock. Usually, a time of the order of 100 milliseconds passes between an actuation request and the complete mechanical change of state of the lock.

However, there are applications in which such a period of time is not available or is not desirable for smooth operation. An example of this is the threaded spindle drive for positioning a trimmable tailplane. In the case of breakage of torque transmitting components in this drive very high spins can occur due to aerodynamic loads on the threaded spindle, which can lead to a flight-critical adjustment of the tailplane within 10 milliseconds.

In order to avoid such a so-called "running away" of the tailplane, it has been proposed in US 6,109,415 to provide the threaded spindle with a return friction brake, however, such return friction brake cause high maintenance costs due to the rapid wear of the friction plates.

Furthermore, the return friction brakes require increased by the friction power drive power. Another disadvantage of such brake assemblies is that the assurance of the function proves to be particularly difficult because of the large Reibwerttoleranzen. The function of the return friction brake can be tested with great effort, the functional test can only be performed under workshop conditions. Therefore, malfunctions caused by real environmental conditions of flight operation, such as icing, can not be detected.

The object of the present invention is therefore to provide a rotation lock, in particular a bidirectionally acting rotation lock, for a shaft arrangement which has a particularly short reaction time.

This object is achieved by a lock with the features of claim 1. Thereafter, it is provided that the rotation lock has at least one mechanical arrangement which is connected to the shaft arrangement or is connectable, the mechanical arrangement being such. is formed that the shaft mechanically locked depending on the spin and in the locked position of the rotation lock. Preferably, the blockage is purely mechanical. The rotation lock is thus able to lock the shaft to be braked at high spin very quickly. The high locking speed is achieved in that it is preferably a purely mechanical Sperrablauf, preferably without the involvement of electrical and / or magnetic processes is. The lock according to the invention is in this case a rotation lock, which acts bidirectionally in a preferred embodiment of the invention.

In a conceivable embodiment of the invention, it is provided that the shaft arrangement communicates with or can be connected to a mechanical arrangement, wherein the mechanical arrangement is constructed such that a mechanical collapse of the barrier can be realized by the action of an axial force or an axial movement that the wave can be blocked within a very short period of time.

The lock according to the invention can preferably be used in a threaded spindle adjusting device for trimming aircraft horizontal stabilizers or other tail units, flaps, rudders, etc., wherein the shaft to be blocked is connected to the threaded spindle such that torque and the axial load can be transmitted.

In a preferred embodiment of the invention, the mechanical arrangement is a spin-sensitive assembly, and has an electromagnet, which is turned off in the blocking position of the rotation lock, in which the rotation of the shaft is suppressed. By switching off the electromagnet can be achieved that the electromagnet to the arrangement exerts no force that would lead to a release of the lock.

Preferably, the mechanical arrangement of the rotation lock according to the invention is in communication with the electromagnet, wherein the mechanical arrangement cooperates with the electromagnet such that a permanent blocking can be realized preferably by one or more springs, without being able to counteract this, since it is preferably provided that it is switched off. When the mechanical assembly is moved to its locked position, the armature of the solenoid moves axially along with the shaft of the mechanical assembly, resulting in a change in current or a change in pulse width modulation (PWM) ratio due to which a shutdown occurs the electromagnet takes place. The electromagnet then no longer counteracts the maintenance of the blocking position, so that the permanent blocking is preferably realized by the use of one or more springs. In the on state, the electromagnet acts in a direction opposite to the force applied by the spring arrangement, ie in the "release direction" of the rotation lock.

It is particularly advantageous that the shaft of the shaft assembly to be braked, the mechanical assembly and the electromagnet are mounted in a common housing, and that the housing is connected to the aircraft structure to initiate the locking torque in this. However, it is also conceivable to use a plurality of housings for the mentioned components.

Preferably, the mechanical arrangement comprises a shaft, which is preferably connected at one of its ends to the shaft to be braked, wherein by means of a coupling wheel rotational form closure between the two waves can be realized, and preferably at the other end, with an inertial mass in such a connection is that preferably from a predetermined threshold torque from the shaft can be introduced into the inertial mass and a distance from the inertial mass, axial movement of the shaft in dependence on the amount of torque and preferably direction-independent is possible.

The inertial mass may be rotatable and be formed for example by a "flywheel" or the like, which rotates with the shaft in normal operation, but is unable to follow when exceeding a limit value of the torque or the rotational acceleration of the rotational movement of the shaft, which it comes to said axial movement of the shaft, which in turn leads to a collapse of the barrier. The shaft of the rotation lock is preferably connected via a coupling wheel and a suspension with the shaft to be braked rotationally fixed and axially displaceable, with a rotational mold closure is feasible. In this case, the shaft to be braked on a preferably cone-like or otherwise formed recess, in which the spring and the coupling wheel can be mounted.

This spring can act on the shaft of the mechanical assembly towards the inertial mass, i. away from the locked position, exerting effective force. The same applies to the electromagnets in its operating state.

It is conceivable that at least one first blocking element is provided, which is preferably movable in the axial direction of this shaft in the direction of movement of the shaft of the mechanical arrangement, and that the shaft to be blocked has at least one second blocking element or is non-rotatably connected thereto, wherein the first with the second blocking element in the blocking position of the rotation lock in such a way with each other that a rotation of the second blocking element is prevented relative to the first blocking element. Preferably, the at least one first blocking element is arranged rotationally fixed, so that in the blocking position the shaft to be blocked is fixed in the direction of rotation.

In this case, the at least one first blocking element and the at least one second blocking element preferably has one or more serrations, which are spaced apart in the release position of the rotational lock and engage in the blocking position of the rotational lock with each other.

It is conceivable for a force, preferably a spring force, to act on the at least one first blocking element in the direction of the at least one second blocking element. This causes in the locked position of the rotation lock a permanent backup of this locking position.

The one or more first locking elements may be directly or indirectly connected to the shaft of the mechanical arrangement in such a way that in In the event that the shaft is moved axially also a movement of the first or the first locking elements is released or takes place, so that the lock is incident. Preferably, the one or more first locking elements or the toothed disks are moved by the force of the spring or spring arrangement.

The blocking elements may for example be designed as toothed disks or have these.

The electromagnet, which is known to consist of a coil, a pot body and an armature is mounted in the fixed housing between the coupling wheel and the flywheel, wherein the axis of rotation of the shaft of the mechanical assembly coincides with the longitudinal axis of the electromagnet, and wherein the armature is mounted with the shaft of the mechanical arrangement by means of a bearing which is capable of transmitting axial forces.

The shaft of the spin-acceleration-sensitive mechanical arrangement is preferably connected to the inertial mass by means of a ball-and-slot arrangement which has at least one ball, the shaft and the inertial mass each having at least one ball slot for receiving the at least one ball. The ball scenes are arranged corresponding to each other.

The ball-and-gate arrangement is preferably held together by the force of the suspension and the magnetic force of the electromagnet. Each ball gate has a shape that ensures rotation of the ball received by it at a constant distance from the axis of rotation of the shaft, with the depth of the ball slide reduced during the rolling of the ball in both directions. It is considered to be particularly advantageous if the at least one ball backdrop in a recess provided in the inertial mass (eg flywheel) recess is formed and the corresponding shaft-side ball backdrop in a substantially semi-conical arrangement, preferably substantially perpendicular to the shaft axis and fixed to the shaft is formed. The ball scenes may preferably have a substantially crescent-shaped cross-section, although other shapes are possible. It is conceivable that the shape of the ball backdrop ensures a rolling of the ball at a constant distance from the axis of rotation.

Furthermore, the gate is preferably shaped such that its depth and thus the "depth of immersion" of the ball during rolling is reduced .. Starting from the lowest point of the ball, the reduction of the slot depth for both directions of rotation is preferably identical.

Preferably, upon acceleration of the shaft, the transmission is brought about on the inertial mass of an acceleration moment corresponding to its inertia, the acceleration moment being initiated by the ball-and-slot arrangement under the action of an axial force.

It is further considered to be particularly preferred if axial movement of the shaft of the mechanical assembly results in movement of the associated armature of the electromagnet and thus during movement to a change in current, supply of the electromagnet with constant voltage, or change in pulse width modulation Ratio, when supplying the electromagnet with constant current by means of PWM current control, leads, so that the solenoid is switched off or is turned off or the power or magnetic force is or is reduced. As a result, the electromagnet applies no or only a smaller force acting in the direction of the inertial mass on the shaft of the mechanical arrangement.

A permanent blocking or securing of the blocking position is preferably realized by a spring arrangement which exerts a force on the one or more first locking elements of the mechanical arrangement in the direction of the second locking element or elements, and thus prevents disengagement of the barrier. It is preferred if a spin acceleration-sensitive, mechanical arrangement according to the invention for a lock, in particular for a rotation lock, a shaft and a ball-and-slot arrangement having at least one rotatably mounted and displaceable ball in a ball backdrop. In this case, the shaft may preferably be non-rotatably and axially displaceable connected at one end with a shaft to be braked and preferably with its other end by means of ball-and-slot arrangement with a rotatable inertial mass (eg a flywheel) are in communication, so that a torque transmission of the shaft on the inertial mass and from a torque exceeding a threshold or rotational acceleration, a distance from the inertial mass, axial movement of the shaft in dependence on the amount of torque can be realized.

The rotation lock according to the invention is preferably used in a brake system for a drive train of slat and landing flap drives or threaded spindle drives for actuating trimable horizontal stabilizers of an aircraft.

A threaded spindle drive for positioning a trimmable tailplane may have at least one rotation lock according to the invention. In this case, the shaft assembly to be braked by the threaded spindle extending in the tie rod of the threaded spindle drive or the threaded spindle itself.

The present invention will now be explained in more detail with reference to an embodiment according to the drawing. The same or comparable components are provided with the same reference numerals in the figures. Show it:

1 shows a sectional view of a rotation lock according to the invention according to an embodiment,

FIG. 1a is an enlarged sectional view in the area of the ball-and-slot arrangement along the line AA according to FIG. 1, FIG. 2 shows a perspective view of a part of the rotation lock according to the invention according to FIG. 1,

Figure 3: a perspective view of a portion of the lock in exploded view and

Figure 4: a perspective view of the locking effect causing toothed pulleys with spring arrangement.

Figure 1 shows a sectional view of a rotation lock 10 according to the invention, which is actuated by means of an electromagnet 150, 160, 170, 180. As shown in FIG. 1, the electromagnet consists of a coil 150, which can also be constructed from a plurality of individual coils, a pot body 160, an armature 170 and a reflux body 180.

A shaft assembly 20 to be braked is partially rotatably supported by a rolling bearing 24 in a housing 100 and consists of a shaft 22 and a toothed sleeve 26, which are interconnected or formed by one and the same part. The shaft assembly 20 may also be mounted by means of a sliding bearing.

The shaft assembly 20 also has - as shown in Figure 3 - two spur gear teeth, for example, with opposite sawtooth on, with other tooth shapes are possible. One of these serrations is located in the end face of said sleeve 26 and a further of these serrations is located in a bushing 26 ^' , which surrounds the shaft 22 and the sleeve 26, as is apparent from Figure 1 and rotatably with the shaft 22 and . is in communication with the socket 26.

Opposite these serrations (ie the second locking elements) are an outer toothed disc 70 and an inner toothed disc 80, which are likewise provided with serrations (ie the first locking elements) and are shaped such that, in the locking position, they are in contact with the serrations of the welders. lenanordnung 20 and the bushes 26, 26 ^' are engaged. The toothed disks 70 and 80, which can also be seen from FIG. 3, are non-rotatably connected via pins 90, but are connected to the stationary housing 100 in an axially displaceable manner. If the first are engaged with the second locking elements, rotational movement of the shaft 22 is blocked; if this is not the case, the first locking elements are rotatable relative to the second locking elements, ie the shaft 22 is rotatable.

In the embodiment shown in Figure 1 is an application of the lock according to the invention in a threaded spindle actuator for trim of aircraft elevator. The shaft can be connected to the threaded spindle such that a torque and the axial load can be transmitted. For this purpose, the housing 100 can be connected to the aircraft structure in order to be able to introduce the axial load and the locking torque into the aircraft structure.

As can be seen in FIG. 1, the armature 170 is attracted by the current-carrying coil 150, i. moved to the right and holds an axial stop 190, the inner toothed disc 80 against the spring force acting on this in the open position, which in turn causes an open position of the outer toothed disc 70 via an axial stop 200 against the force acting on this spring force. The spring force on the toothed discs 70, 80 is applied by the springs 110, 120, 130, 140.

FIG. 3 shows the spring arrangements 110, 120, 130, 140 which exert a force on the toothed disks 70 and 80 which acts in the direction of the opposite end toothings of the bushings 26, 26 ^' .

The toothed disks 70 and 80 are rotatably connected via pins 90, but axially displaceably connected to the stationary housing 100. The outer toothed disk 70 is acted upon by a plurality of springs 110 in the direction of the opposite toothing (see Figure 4), wherein the force is transmitted by spring plates 120 which pass through bores provided in the inner toothed disc 80. Accordingly, the inner toothed disc 80 is acted upon by a plurality of springs 130 in the direction of the opposite toothing with force. strikes, wherein the force of spring plates 140 is transmitted directly to the inner toothed disc 80.

In the open state, as shown in Figure 1, the toothed discs 70 and 80 are not engaged with their opposite teeth, since they are retained by an electromagnet and / or by the spring 220 acting on the shaft 220.

In order to prevent that the spur gear interferes with each other during the engagement process, it is advantageous if in the open position of the barrier, the axial distance that covers the inner sprocket 80 to its full engagement with its opposite teeth is at least twice as large such as the axial travel required by the outer sprocket 70 to its full engagement with its opposing teeth.

If the energization of the coil 150 is interrupted and the shaft 22 counteracted with torque in the counterclockwise direction (same viewing direction in Figure 3), it can rotate until the inner spur gear is engaged and completed the rotation form-fitting. The external teeth do not hinder this rotation, because the saw teeth slide off each other due to their orientation. Is the above rotation of the shaft 22 terminated due to engagement of the inner star teeth, so also the outer spur gearing has reached a rotational position to each other, which causes these also engages each other in consequence of their spring force. The shaft assembly 20 is thus free of play blocked in both directions of rotation.

Upon rotation of the shaft 22 in the clockwise direction, the blocking takes place in both directions, but the sequence of engagement of the inner and outer teeth is reversed.

The shaft 20 has a recess, which is formed, for example, cone-shaped or in another form and in which a coupling wheel 210 and a spring 260 is mounted. The clutch gear 210 has an external plug-in tion, so that this produces a rotational form fit with a corresponding internal splines of the shaft 20.

Furthermore, the coupling wheel 210 has an internal spline, so that it is rotatably mounted with a shaft 220 of the spin-sensitive mechanical arrangement according to the invention.

Thus, a rotational mold closure between the shaft 22 and the shaft 220 is made, wherein also an axial movement of the shaft 220 and the application of a force by means of the spring 260 can be realized.

The axis of rotation 220 ^'of the shaft 220 coincides with the longitudinal axis of the electromagnet whose armature 170 is connected to the shaft 220 by means of rotary bearings 30.

The shaft 220 is connected at its other end by means of a ball-and-gate arrangement 240, 250, which is shown in more detail in Figures 1a and 2, with a rotatable inertial mass, for example with a flywheel 230.

The ball-and-slotted assembly 240, 250 is thus held together by spring and magnetic force, so that a torque transmission from the shaft 220 in the inertial mass 230 and a moving away from the inertial mass 230, axial movement of the shaft 220 as a function of height of the torque, but regardless of the direction guaranteed.

The ball-and-gate arrangement 240, 250 consists in this embodiment, as shown in Figure 2, of three balls 240 and three ball slides 250. The shape of the ball slides 250 is shown in more detail in the perspective view of FIG.

The ball splines 250 are on the shaft side in a hemispherical arrangement, which is connected substantially perpendicular to the shaft axis 220 'fixed to the shaft 220, formed and have a substantially crescent-shaped cross-section. The shape of the ball slide 250 ensures that the ball 240 rolls at a constant distance from the axis of rotation of the shaft 220. The depth of the ball slide, and thus the depth of insertion of the ball 240 during rolling, is reduced from the lowest point of the ball 240 the reduction of the slot depth is identical for both directions of rotation.

As shown in the enlarged sectional view according to FIG. 1a, the inertial mass or the flywheel 230 has in each case one recess corresponding to the ball slot 250 shown in FIG. 2, which is also referred to below as a ball slot 250. The two opposing ball scenes 250 of the shaft 220 and the inertial mass 230 each receive a ball 240.

The shaft 220 and the inertial mass 230 are held in axial contact with the balls 240 by the spring 260 and by the electromagnetic force exerted on the armature 170 connected to the shaft 220 when the coil 150 is energized. Thus, the ball-and-gate arrangement 240, 250 is held together by the spring force of the spring 260 and by the magnetic force acting on it.

If the shaft 22 is accelerated, the inertial mass 230 requires an acceleration moment corresponding to its mass inertia. This is initiated by the ball-and-slot arrangement 240, 250, which in turn requires axial force.

If the required axial force is too low, there is an axial movement of the shaft 220 and caused by it, a collapse of the lock. However, the axial movement of the shaft 220 also causes the associated armature 170 of the electromagnet to move along and the lock to occur, i. the serrations of the shaft assembly 20 and the toothed discs 70, 80 are engaged, whereby the rotation of the shaft 22 is prevented.

The movement of the armature 170 of the electromagnet during the movement leads to a change in the current intensity when the electromagnet is supplied with a constant voltage or to a change in the PWM ratio (pulse width modulation ratio), when the electromagnet is supplied with constant current. tem current by means of PWM current control. Due to this, the electromagnet is turned off.

The rotation lock according to the invention additionally has a conventional monitoring to detect a malfunction. Thus, a discrepancy can be detected by continuously comparing the commanded rotational position of the shaft 22 to be braked with the actual rotational position measured by a rotational angle sensor 270 associated with the barrier 10. As a result, the solenoid is turned off and thus brought about the blocking.

If the acceleration of the shaft 22 is too low for a response of the spin-sensitive mechanism, the shutdown is performed by this monitoring function.

By reducing the magnitude of the current flowing through the electromagnet, the magnetic force, and thus the spin acceleration required for the locking, can be reduced. This can be advantageously used to check the arrangement in such a way that the current intensity is reduced such that the maximum spin, which can be generated regularly by the drive of the spindle, is sufficient to cause the rotation lock to engage. There is thus no access to the threaded spindle actuator required and the test can be carried out automatically.

Advantageously, this functional test is carried out immediately after landing of the aircraft, for example during taxiing of the aircraft to its stand, since at this time the probability is high that an optionally existing, dysfunctional icing within the actuator is still present.

Claims

Anti-rotation patent claims

1. A rotation lock, in particular bidirectionally acting rotation lock, for a shaft assembly (20) having at least one shaft (22), characterized in that the rotation lock has at least one mechanical arrangement which communicates with the shaft assembly (20) or is connectable, wherein the mechanical arrangement is designed such that it mechanically blocks the shaft (22) as a function of rotational acceleration and in the blocking position of the rotational lock.

2. Rotary lock according to claim 1, characterized in that the at least one mechanical arrangement is constructed such that by action of an axial force or by a movement in the direction of the shaft axis (22), a mechanical collapse of the lock can be realized.

3. Rotary lock according to claim 1 or 2, characterized in that an electromagnet (150, 160, 170, 180) is provided, which is arranged and controlled such that the electromagnet (150, 160, 170, 180) on the mechanical arrangement in the blocking position of the rotation lock exerts no force or no force acting in the opening direction of the rotation lock.

Rotary lock according to Claim 3, characterized in that the shaft (22) of the shaft arrangement (20) to be blocked, the mechanical arrangement and the electromagnet (150, 160, 170, 180) are arranged in a common housing (100) or in separate housings ,

Rotary lock according to one of the preceding claims, characterized in that the mechanical arrangement comprises a shaft (220) which is rotationally fixed in a region, preferably at one end with the shaft to be blocked (22), wherein preferably a rotational mold closure is feasible, and in a further region, preferably at the other end with an inertial mass (230) in such a way that a torque from the shaft (220) in the inertial mass (230) can be introduced, and one of the inertial mass ( 230) removing, axial movement of the shaft (220) in dependence on the magnitude of the torque and preferably takes place independently of direction.

Rotary lock according to claim 5, characterized in that the shaft (220) via a coupling wheel (210) with the shaft (22) is rotationally fixed and axially displaceable, wherein by means of the coupling wheel (210) rotationally positive connection between the shaft (220) and the shaft (22) is realized.

Rotary lock according to claim 5 or 6, characterized in that at least one first blocking element (70, 80) is provided, which is movable in the direction of movement of the shaft (220), and that the shaft to be blocked (22) has at least one second blocking element or with communicating therewith, wherein the first (70, 80) communicates with the second blocking element in the blocking position of the rotation lock in such a way that a rotation of the second blocking element relative to the first blocking element (70, 80) is prevented, preferably pre - it can be seen that the first (70, 80) and / or the second blocking element have spur gears, which engage in the locking position of the rotational lock with each other.

8. rotation lock according to one of claims 5 to 7, characterized in that the shaft (220) in the axial direction by at least one spring (260) is loaded.

9. Rotary lock according to one of claims 5 to 8, characterized in that the electromagnet (150, 160, 170, 180) having an armature (170) in the housing (100) between the coupling wheel (210) and the inertial mass (230) is mounted, wherein the axis of rotation of the shaft (220) with the longitudinal axis of the electromagnet (150, 160, 170, 180) coincides, and wherein the armature (170) is connected to the shaft (220) by means of a storage.

10. Rotary lock according to one of claims 5 to 9, characterized in that the shaft (220) by means of a ball-and-slide arrangement (240, 250) which has at least one ball (240) with the inertial mass (230) in Connection is, wherein the shaft (220) and the inertial mass (230) each have at least one ball link (250) for receiving the ball (240), wherein the respective ball links (250) are arranged corresponding to each other, and wherein the ball-and-gate arrangement (240, 250) is held together or held together by the force of the suspension (260) and the magnetic force of the electromagnet (150, 160, 170, 180).

11. Rotary lock according to claim 10, characterized in that the ball link (250) has a shape which ensures rotation of the ball (240) at a preferably constant distance from the axis of rotation of the shaft (220), wherein the depth of the ball -Bulisse (250) in the direction of the rolling movement of the ball (240) starting from the lowest point in at least one, preferably reduced in both directions.

12. Rotary lock according to claim 10 or 11, characterized in that an acceleration of the shaft (22) causes a transmission of the torque to the inertial mass (230), wherein the acceleration torque of the ball-and-gate arrangement (240, 250) is initiated ,

13. Rotary lock according to one of claims 5 to 12, characterized in that it is designed such that an axial movement of the shaft (220) to a movement of the associated armature (170) of the electromagnet (150, 160, 170, 180) and preferably leads to a change in the current or to a change in the pulse width modulation ratio, due to which the solenoid (150, 160, 170, 180) is turned off.

14. Rotary lock according to one of the preceding claims, characterized in that at least one spring arrangement (110, 120, 130, 140) is provided which exerts a force on the rotation lock such that it is preferably permanently fixed in its locking position, preferably provided in that the spring arrangement acts on the one or more first blocking elements (70, 80) in such a way that they are loaded in the direction towards the second blocking element.

15. A method for checking a malfunction by means of a rotation lock according to one of claims 1 to 14, characterized in that upon detection of a discrepancy between commanded rotational position of the shaft (22) and preferably by means of a rotation angle sensor (270) measured actual rotational position of the shaft (22 ) the electromagnet (150, 160, 170, 180) is turned off, so that the rotation lock falls into the blocking position.

16. A method of checking a rotation lock according to any one of claims 1 to 14, characterized in that the method comprises the step of reducing the force generated by the electromagnet, so that the regular from the drive unit of the shaft assembly (20) applied spin to a collapse the lock leads.

17. The method according to claim 15 or 16, characterized in that the check is carried out after landing of the aircraft, in particular of the aircraft, preferably during the taxiing of the aircraft to its stand.

18. Use of a rotation lock according to one of claims 1 to 14 for blocking a horizontal stabilizer of an aircraft, in particular a controlled by a trimmable horizontal stabilizer actuator (THSA) tailplane of an aircraft.

19. Aircraft, in particular aircraft, with at least one rotation lock according to one of claims 1 to 14 and / or means for carrying out one or both methods according to claims 16 to 18.

20. Aircraft according to claim 19, characterized in that the rotation lock with a drive train of one or more slats and flapper drives or other damper drives and / or with one or more threaded spindle drives for the operation of trimmable horizontal stabilizers or other flaps and tail of the aircraft is so in communication in that the drive train or the threaded spindle drive can be blocked by the rotation lock in its direction of rotation.