Patent Description:
<CIT> discloses a hatch locking device which can be used in the aerospace field.

Aircraft doors in a fuselage cell of an aircraft must transfer considerable peripheral loads. The greater the diameter of a fuselage cell the higher are the peripheral loads which arise in the fuselage cell structure. The load transfer between the aircraft door and the fuselage cell structure is commonly provided through a multiple of hooks swivel mounted on a shaft which engage round substantially horizontally fixed shaft sections in the area of the fuselage cell.

High tensile forces act during the flight, in particular, in the case of relatively large aircraft doors or hatches, such as cargo hold hatches, for example. In addition, high load differences, for example in comparison between an unloaded and loaded cargo hold, can lead on ground to deformations or deflections occurring in the region of the hatch gaps, which deformations or deflections can impair the correct orientation of the hatch locking elements with respect to one another.

Aspects of the invention may provide solutions for improving locking and securing of aircraft or spacecraft doors under different loads.

According to the invention, this problem is solved in each case by the subject matters of the independent claims.

According to a first aspect of the invention, a hatch locking device for an aircraft or spacecraft hatch is provided. The hatch locking device comprises a drivable spindle drive which extends in a longitudinal axis and is fixed in relation to a hatch frame of the aircraft or spacecraft hatch along the longitudinal axis. Furthermore, the hatch locking device comprises at least one locking bolt which is driven by the drivable spindle drive and is guided along the longitudinal axis and at least one adjustment bush assembly being mounted on a fuselage frame. The at least one adjustment bush assembly comprises a first eccentric bush having a bolt receptacle which is oriented centrally along the longitudinal axis for receiving the at least one locking bolt such that the hatch locking device is positive-locking connectable in two axles both being perpendicular to the longitudinal axis.

According to a second aspect of the invention, an aircraft hatch or an spacecraft hatch comprising a hatch frame and a hatch locking device according to the invention is provided. The hatch locking device is mounted to the hatch frame, wherein the drivable spindle drive is fixed in relation to the hatch frame along the longitudinal axis. Furthermore, the aircraft hatch or the spacecraft hatch comprises a drive unit which is mounted to the hatch frame and drives the drivable spindle drive.

According to a third aspect of the invention, an aircraft or spacecraft comprising an aircraft hatch or an spacecraft hatch according to the invention is provided.

A fundamental concept of the invention is to provide a bolt closure for an aircraft hatch, which bolt closure can have a positive-locking connection in at least two directions as well as one-way in a third direction, in particular in Y- and Z-direction as well as in +X-direction. That means in X-direction the positive-locking connection can only be provided in pushing direction of the locking bolt to the adjustment bush assembly. Moreover, the bolt closure can transmit forces in X-, Y-and Z-direction and torques, or also called moments, in Y- and Z-direction in case of movement of the aircraft or spacecraft hatch in relation to the fuselage frame by loads during flight, for example, or in case of self-centering during a locking process in case of misalignment caused by loading differences, for example. Furthermore, the spindle drive and the adjustment bush assembly can be mounted reversely.

A particular advantage in the solution according to an aspect of the invention is that manufacturing tolerances of the hatch panel and/or the hatch frame can be compensated for translationally in all directions by the adjustable bush assembly; the hatch locking device makes self-centering of the hatch during closure and self-centering of the locking bolt during locking possible by the conical bush reception. In addition, one particular advantage results from the screw drive actuation which has high power and increases the reliability of the locking and unlocking. Moreover, the drivable spindle drive is self-securing.

Advantageous embodiments and further developments emerge from the description with reference to the figures.

According to some aspects of the hatch locking device according to the invention, the at least one locking bolt comprises two opposing locking bolts which are driven by the drivable spindle drive and are guided along the longitudinal axis, and wherein the at least one adjustment bush assembly comprises two adjustment bush assemblies each being mounted on a fuselage frame. Both locking bolts are driven by the drivable spindle drive simultaneously. Therefore, one of the two locking bolts can comprise a left-hand thread, wherein the other locking bolt can comprise a right-hand thread.

According to some further aspects of the hatch locking device according to the invention, the two adjustment bush assemblies are configured to receive the two opposing locking bolts such that the hatch locking device is positive-locking connectable in the longitudinal axis. Thus, the hatch locking device can have a positive-locking connection in all directions, in particular in X-, Y- and Z-direction, wherein the longitudinal axis represents the X-direction. The hatch locking device cannot pop out of a locked position.

According to some further aspects of the hatch locking device according to the invention, an end region of the at least one locking bolt is encased in a bolt bush, wherein the bolt bush slides inside the drivable spindle drive for supporting the at least one locking bolt against a torque perpendicular to the longitudinal axis. Higher torques can be withstood thereby. The end region of the at least one locking bolt provides a higher leverage to the hatch frame than the thread of the drivable spindle drive.

According to some further aspects of the hatch locking device according to the invention, the at least one adjustment bush assembly further comprises a second eccentric bush which partly surrounds the first eccentric bush on its outer surface, wherein the first eccentric bush and the second eccentric bush each basically comprise a same axle offset. Thus, the axle offset of each eccentric bush can be combined to provide many different positions for the bolt receptacle to receive the locking bolt in case the longitudinal axis of the hatch locking device is offset to the longitudinal axis of the adjustment bush assembly. Furthermore, in case the longitudinal axis of the hatch locking device corresponds to the longitudinal axis of the adjustment bush assembly, the first eccentric bush and the second eccentric bush both having the same axle offset can be balanced out such that the axle offset provided by the first eccentric bush is compensated by the axle offset of the second eccentric bush.

According to some further aspects of the hatch locking device according to the invention, the second eccentric bush has a conical shape and comprises teeth on a front side for rotating the second eccentric bush in relation to the first eccentric bush, wherein the at least one adjustment bush assembly further comprises a nut interacting with the first eccentric bush for pressing the second eccentric bush between the first eccentric bush and the fuselage frame. Thus, the conical shape can increase the axial load capability. The radial preload prevents the adjustment bush assembly from rotating as a result of the torque caused by the transverse force and eccentricity or as a result of the friction between the locking bolt and the first eccentric bush. Hence, a continuous adjustment of the offset of the first eccentric bush and the second eccentric bush can be provided. The centric recess of the second eccentric bush assist to rotate the second eccentric bush in relation to the first eccentric bush. Furthermore, an axial adjustment of the locking bolt in relation to the first eccentric bush can be provided by a selection of the first eccentric bush with an appropriate inner diameter.

According to some further aspects of the hatch locking device according to the invention, wherein the at least one adjustment bush assembly further comprises a shim washer for adapting a distance between the at least one locking bolt and the first eccentric bush along the longitudinal axis.

According to some further aspects of the hatch locking device according to the invention, the first eccentric bush is configured as a serrated, conical eccentric bush and comprises teeth on a front side for avoiding a rotation of the serrated, conical eccentric bush in relation to the fuselage frame. That means the first eccentric bush has an outer conical shape and comprises teeth on a front side for avoiding a rotation in relation to the second conical bush whereby the second conical bush is rotationally fixed in relation to the fuselage frame by serration. Furthermore, an axial adjustment of the locking bolt in relation to the first eccentric bush can be provided by a selection of the first eccentric bush with an appropriate inner diameter.

According to some aspects the aircraft or spacecraft hatch according to the invention comprises at least two hatch locking devices, wherein at least one hatch locking device comprises two opposing locking bolts and wherein at least one hatch locking device comprises one locking bolt. The hatch locking device with one locking bolt can be arranged at a lateral side of the aircraft or spacecraft hatch, wherein the lateral side extends along the orientation of the fuselage frame. The hatch locking device with two locking bolts can be arranged at a horizontal side of the aircraft or spacecraft hatch, wherein the horizontal side extends perpendicular to the orientation of the fuselage frame. Therefore, the hatch locking device with two locking bolts can be arranged in relation to the fuselage frame such that both adjustment bush assemblies can be supported by two fuselage frames, one fuselage frame being on each side.

According to some further aspects the aircraft or spacecraft hatch according to the invention further comprises a drive system which mechanically couples the drive unit with the hatch locking device, wherein the drive system comprises at least one of the following: a main drive shaft, a drive belt or a worm drive. Thus, the drive unit does not need to be arranged next to the hatch locking device. In particular when the aircraft hatch comprises more than one hatch locking device the drive system can couple each hatch locking device to the drive unit.

According to some further aspects the aircraft or spacecraft hatch according to the invention further comprises a pull-in device for forcing the aircraft or spacecraft hatch to close, wherein the pull-in device comprises a hollow cam disc which is mechanically coupled to the drive system and configured to interact with a pin being mounted on a fuselage frame. Due to different loading conditions the aircraft or spacecraft hatch might not close completely without assistance. Instead small gaps between the fuselage frame and the aircraft or spacecraft hatch can remain such that the locking bolt can not be received in the first eccentric bush. In particular, the pull-in device can be used when the small gaps have a distance from the pin to the hollow cam disc of <NUM> or less, preferably of <NUM> or less. In other words, the pull-in device can be used when the misalignment between the pin and the hollow cam disc is <NUM> or less. Therefore, the pull-in device is configured to interact with the pin to completely close the aircraft or spacecraft hatch and to align the locking bolt to the bolt receptacle of the first eccentric bush.

According to some further aspects of the aircraft or spacecraft hatch according to the invention, the pull-in device further comprises a planetary gear arranged between the hollow cam disc and the drive system for synchronizing the rotation of the hollow cam disc and the rotation of the drivable spindle drive such that the aircraft or spacecraft hatch is at least almost closed before the bolt receptacle receives the locking bolt. The planetary gear increases the torque and hence the pull-in force.

According to some aspects of the aircraft or spacecraft according to the invention, the aircraft or spacecraft hatch is configured as a cargo hold hatch.

The present invention is explained more specifically below on the basis of the exemplary embodiments indicated in the schematic figures, in which:.

The accompanying figures are intended to convey a further understanding of the embodiments of the invention. They illustrate embodiments and are used in conjunction with the description to explain principles and concepts of the invention. Other embodiments and many of the cited advantages emerge in light of the drawings. The elements of the drawings are not necessarily shown to scale in relation to one another. Direction-indicating terminology such as for example "at the top", "at the bottom", "on the left", "on the right", "above", "below", "horizontally", "vertically", "at the front", "at the rear" and similar statements are merely used for explanatory purposes and do not serve to restrict the generality to specific configurations as shown in the figures.

In the figures of the drawing, elements, features and components that are the same, have the same function and have the same effect are each provided with the same reference signs - unless explained otherwise.

<FIG> shows a schematic illustration of a hatch locking device <NUM> with two opposing locking bolts <NUM> in a locked condition. In the illustrated locked condition, the hatch locking device <NUM> is integrated in an aircraft hatch <NUM> and locked to a fuselage frame <NUM>.

The hatch locking device <NUM> comprises a drivable spindle drive <NUM> which extends in a longitudinal axis X. The drivable spindle drive <NUM> is fixed in relation to a hatch frame <NUM> of the aircraft hatch <NUM> along the longitudinal axis X. In particular, the drivable spindle drive <NUM> is arranged between two adjacent hatch frames <NUM>.

Thereby, the drivable spindle drive <NUM> is mounted to the two adjacent hatch frames <NUM> by means of a roller bearing <NUM>, which is supported by the hatch frame <NUM>. Preferably, the roller bearing <NUM> is tapered. Furthermore, the drivable spindle drive <NUM> comprises a spur gear which is engaged with a drive system <NUM> of the aircraft hatch <NUM>. In <FIG>, the drive system <NUM> comprises a spur gear configured to be engaged with the spur gear of the drivable spindle drive <NUM>, for example.

Further, the hatch locking device <NUM> comprises the two opposing locking bolts <NUM> which are driven by the drivable spindle drive <NUM>. A head region of the two locking bolts <NUM> contains a conical shape. The two opposing locking bolts <NUM> are guided along the longitudinal axis X. For driving the two opposing locking bolts <NUM> the drivable spindle drive <NUM> is rotated about the longitudinal axis X. Therefore, one of the two locking bolts <NUM> contains a left-hand thread, wherein the other locking bolt <NUM> contains a right-hand thread. For example, the downwards oriented locking bolt <NUM> contains the left-hand thread and the upwards oriented locking bolt <NUM> contains the right-hand thread, as it is illustrated in <FIG>. Furthermore, the drivable spindle drive <NUM> is self-securing, which means the locking bolts <NUM> are not able to drive the drivable spindle drive <NUM>. Optionally, the drivable spindle drive <NUM> comprises a trapezoidal inner thread and the two locking bolts <NUM> comprise a corresponding trapezoidal outer thread.

Additionally, the hatch locking device <NUM> comprises two adjustment bush assemblies <NUM> each being mounted on the fuselage frame <NUM>. The two adjustment bush assemblies <NUM> are configured to receive the two opposing locking bolts <NUM> such that the hatch locking device <NUM> is positive-locking connectable in the longitudinal axis X and in two axles Y, Z both being perpendicular to the longitudinal axis X.

Each adjustment bush assembly <NUM> comprises a first eccentric bush <NUM>. The first eccentric bush <NUM> contains a bolt receptacle <NUM> which is oriented centrally along the longitudinal axis X for receiving the locking bolt <NUM> such that the hatch locking device <NUM> is positive-locking connectable in all directions, i.e. the axles X, Y and Z. The bolt receptacle <NUM> has a conical shape corresponding to the conical shape of the locking bolt <NUM>. In this embodiment, the first eccentric bush <NUM> contains a cylindrical shell surface, but is not limited to such a shape.

Moreover, each adjustment bush assembly <NUM> comprises a second eccentric bush <NUM>. The second eccentric bush <NUM> partly surrounds the first eccentric bush <NUM> on its outer surface. Preferably, the first eccentric bush <NUM> and the second eccentric bush <NUM> each basically comprise a same axle offset.

Each adjustment bush assembly <NUM> further comprises a shim washer <NUM> for adapting a distance between the at least one locking bolt <NUM> and the first eccentric bush <NUM> along the longitudinal axis X. For example, the adjustment bush assembly <NUM> includes at least one fastening screw for fastening the adjustment bush assembly <NUM> or the first eccentric bush <NUM> at the fuselage frame <NUM>. The fastening screw is oriented parallel to the longitudinal axis X. By varying a thickness of the shim washer <NUM> the first eccentric bush <NUM> can be positioned closer to or further away from the locking bolt <NUM>. At an installation of the hatch locking device <NUM> the thickness of the shim washer can be chosen such that the two opposing locking bolts <NUM> are received in the first eccentric bushes <NUM> basically at the same time. That means depending on manufacturing tolerances of the fuselage frame <NUM> and the hatch frame <NUM>, respectively, the shim washer <NUM> compensates a distance along the longitudinal axis X.

Furthermore, axial forces are transferred by the conical shape of the locking bolt <NUM> via the drivable spindle drive <NUM> and via the tapered roller bearing <NUM> to the hatch frame <NUM>. Alternatively or additionally, the two opposing locking bolts <NUM> are arranged between two adjacent hatch frames <NUM>.

Further, an end region of the locking bolt <NUM> can be encased in a bolt bush <NUM>, as illustrated in <FIG>. The bolt bush <NUM> can slide inside the drivable spindle drive <NUM> for supporting the locking bolt <NUM> against a torque perpendicular to the longitudinal axis X.

Preferably, the hatch frame <NUM> houses a hatch bush <NUM> which is penetrated by the slidable locking bolt <NUM>. In particular, the hatch bush <NUM> is fixed in relation to the hatch frame <NUM>.

Optionally, the locking bolt <NUM> comprises a groove <NUM> oriented along the longitudinal axis X for securing the locking bolt <NUM> against rotation around the longitudinal axis X. Thereby, a bolt or a pin <NUM> causes a positive-locking connection between the locking bolt <NUM>, the hatch bush <NUM> and the hatch frame <NUM> when being inserted into the groove <NUM> through the hatch bush <NUM> and the hatch frame <NUM>, as it is illustrated in view A-A in <FIG>.

<FIG> shows a schematic illustration of an adjustment bush assembly <NUM> of a hatch locking device <NUM>.

The adjustment bush assembly <NUM> of <FIG> differs from the adjustment bush assembly of <FIG> in that the first eccentric bush <NUM> is configured as a serrated, conical eccentric bush. The first serrated, conical eccentric bush <NUM> comprises teeth <NUM> on a front side of the serrated, conical eccentric bush <NUM> for avoiding a rotation of the serrated, conical eccentric bush <NUM> in relation to a fuselage frame <NUM>.

Further, the second eccentric bush <NUM> is configured as serrated, conical eccentric bush. The second serrated, conical eccentric bush <NUM> comprises teeth <NUM> on a front side and on a back side of the serrated, conical eccentric bush <NUM>.

The first serrated, conical eccentric bush <NUM> and the second serrated, conical eccentric bush <NUM> are oriented along the longitudinal axis X.

The teeth <NUM> are arranged circumferential around the first serrated, conical eccentric bush <NUM> and the second serrated, conical eccentric bush <NUM>, respectively. The first serrated, conical eccentric bush <NUM> and the second serrated conical eccentric bush <NUM> are mounted to the fuselage frame <NUM> by means of a serrated plate <NUM>. The serrated plate <NUM> contains corresponding teeth <NUM> for engaging with the teeth <NUM> of the eccentric bushes <NUM>, <NUM>. Thereby, the teeth <NUM> preferably are configured to provide a small adjustable rotation step of the first serrated, conical eccentric bush <NUM> in relation to the serrated plate <NUM> and of the second serrated, conical eccentric bush <NUM> in relation to the serrated plate <NUM>. The serrated plate <NUM> can be mounted to the first eccentric bush <NUM> and axially fixed by a plate mounted to the fuselage frame <NUM> by means of a fastening screw or the like. For example, the serrated plate <NUM> on the left-hand side can be screwed to the fuselage frame <NUM>. Then the second serrated conical eccentric bush <NUM> can be mounted to the fuselage frame <NUM>. After that, the serrated plate <NUM> on the right-hand side can be mounted interacting with the second serrated conical eccentric bush <NUM>. Finally, the first serrated, conical eccentric bush <NUM> can be mounted interacting with the serrated plate <NUM> on the right-hand side in <FIG>.

For example, a bore of the fuselage frame <NUM> in which the adjustment bush assembly <NUM> is mounted is reference for interlocking of the fuselage frame <NUM> and the second serrated, conical eccentric bush <NUM>. The bore in the second serrated, conical eccentric bush <NUM> is reference for interlocking of the first and second serrated, conical eccentric bush <NUM>, <NUM> and the serrated plate <NUM> on the left-hand and the right-hand side.

The locking bolt <NUM> is receivable in the bolt receptacle of the first serrated, conical eccentric bush <NUM>.

<FIG> shows a schematic illustration of another adjustment bush assembly <NUM> of a hatch locking device <NUM>.

The adjustment bush assembly <NUM> of <FIG> differs from the adjustment bush assembly of <FIG> in that the second eccentric bush <NUM> has a conical shape. Furthermore, the second eccentric bush <NUM> comprises teeth <NUM> on a front side of the second eccentric bush <NUM> for rotating the second eccentric bush <NUM> in relation to the first eccentric bush <NUM>. The teeth <NUM> are arranged circumferential around the second eccentric bush <NUM>.

Optionally, the adjustment bush assembly <NUM> further comprises a nut <NUM> interacting with the first eccentric bush <NUM> for pressing the second eccentric bush <NUM> between the first eccentric bush and a fuselage frame <NUM>.

For countering the nut <NUM> the first eccentric bush <NUM> contains a polygon socket, in particular a hexagon socket.

The first eccentric bush <NUM> and the second eccentric bush <NUM> are oriented along the longitudinal axis X.

The locking bolt <NUM> is receivable in the bolt receptacle of the first eccentric bush <NUM>.

<FIG> show a schematic illustration of an aircraft hatch <NUM> with a pull-in device <NUM>, wherein <FIG> shows the pull-in device <NUM> in a starting condition and <FIG> shows the pull-in device <NUM> in a final condition.

The aircraft hatch <NUM> comprises a hatch frame <NUM>, a hatch locking device <NUM>, a drive unit <NUM> and a drive system <NUM>.

The hatch locking device <NUM> is mounted to the hatch frame <NUM>. A drivable spindle drive <NUM> of the hatch locking device <NUM> is fixed in relation to the hatch frame <NUM> along the longitudinal axis X.

The drive unit <NUM> (not shown in <FIG>) is mounted to the hatch frame <NUM> and drives the drivable spindle drive <NUM>.

The drive system <NUM> mechanically couples the drive unit <NUM> with the hatch locking device <NUM>. Therefore, the drive system <NUM> comprises a main drive shaft.

The pull-in device <NUM> is configured to force the aircraft hatch <NUM> to close. Thereby, the pull-in device <NUM> comprises a hollow cam disc <NUM>. The hollow cam disc <NUM> is mechanically coupled to the drive system <NUM> and configured to interact with a pin <NUM> mounted on a fuselage frame <NUM>.

Further the pull-in device <NUM> comprises a planetary gear <NUM>. The planetary gear <NUM> is arranged between the hollow cam disc <NUM> and the drive system <NUM> for synchronizing the rotation of the hollow cam disc <NUM> and the rotation of the drivable spindle drive <NUM> such that the aircraft hatch <NUM> is at least almost closed before the bolt receptacle <NUM> receives the locking bolt <NUM>.

In the starting condition the hollow cam disk <NUM> is configured to come in close vicinity of the pin <NUM>. The longitudinal axis X of the hatch locking device <NUM> is offset to a longitudinal axis of the first eccentric bush <NUM>, wherein the offset is more than an offset which can be fixed by self-centering of the conical locking bolt <NUM>. Therefore, the locking bolt <NUM> is not able to be driven into the bolt receptacle of the first eccentric bush <NUM>. The drive system <NUM> is in a reference position having an angle of <NUM>° of a rotational axis, as it is illustrated in <FIG>.

Between the starting condition and the final condition the hollow cam disk <NUM> engages behind the pin <NUM> and pulls the aircraft hatch <NUM> towards the fuselage frame <NUM>.

In the final condition of the pull-in device <NUM> the longitudinal axis X of the locking bolt <NUM> basically corresponds to the longitudinal axis of the first eccentric bush <NUM>. Thereby, basically includes the offset of both longitudinal axles less than an offset which can be fixed by self-centering of the conical locking bolt <NUM>. Thus, the locking bolt <NUM> can be driven into the bolt receptacle <NUM> in the final condition, as it is indicated in <FIG>.

In a locked position of the locking bolt <NUM> there is a gap between the hollow cam disc <NUM> and the pin <NUM>. Hence, there is no load on the hollow cam disc <NUM> in the locked position.

<FIG> shows a schematic illustration of an aircraft hatch <NUM> with six hatch locking devices <NUM> each having one locking bolt <NUM> and with three hatch locking devices <NUM> each having two opposing locking bolts <NUM>.

The aircraft hatch <NUM> is attached by a hinge to a fuselage of an aircraft. Preferably, the aircraft hatch <NUM> is attached on one side of the aircraft hatch <NUM> to the fuselage. More particularly, the aircraft hatch <NUM> is attached by a multi-part hinge, and swivels outwards during the opening movement.

The six hatch locking devices <NUM> with one locking bolt <NUM> are exemplarily arranged at a lateral side of the aircraft hatch, wherein the lateral side extends along the orientation of a fuselage frame <NUM>. The three hatch locking devices <NUM> with two locking bolts <NUM> are arranged at a horizontal side of the aircraft hatch being not the hinged side, wherein the horizontal side extends perpendicular to the orientation of the fuselage frame <NUM>.

Further, the aircraft hatch <NUM> comprises a drive system <NUM> which mechanically couples the drive unit <NUM> with the hatch locking devices <NUM>. Thereby, the drive system <NUM> comprises a main drive shaft configured to mechanically couple the three hatch locking devices <NUM> with two opposing locking bolts <NUM>. Furthermore, the drive system <NUM> comprises two drive belts <NUM> configured to mechanically couple the main drive shaft <NUM> with the hatch locking devices <NUM> with one locking bolt <NUM>. Alternatively or additionally, the drive system <NUM> can comprise a worm drive for mechanically coupling the drive unit <NUM> to the hatch locking devices <NUM>.

The aircraft hatch <NUM> and the hatch locking device <NUM>, respectively, can transfer radial forces to align surfaces under cabin pressure. Moreover, they can transfer shear loads to stiffen a door cut-out and can transfer compressive forces along the longitudinal axis X to prevent clash.

<FIG> shows a schematic illustration of an aircraft A with an aircraft hatch <NUM> comprising a hatch locking device <NUM>. Optionally, the aircraft hatch <NUM> is configured as a cargo hold hatch.

In the detailed description above, various features have been combined in one or more examples in order to improve the rigorousness of the illustration. However, it should be clear in this case that the above description is of merely illustrative but in no way restrictive nature. It serves to cover all alternatives, modifications and equivalents of the various features and exemplary embodiments. Many other examples will be immediately and directly clear to a person skilled in the art on the basis of his knowledge in the art in consideration of the above description.

The exemplary embodiments have been chosen and described in order to be able to present the principles underlying the invention and their application possibilities in practice in the best possible way. As a result, those skilled in the art can optimally modify and utilize the invention and its various exemplary embodiments with regard to the intended purpose of use. In the claims and the description, the terms "including" and "having" are used as neutral linguistic concepts for the corresponding terms "comprising". Furthermore, use of the terms "a", "an" and "one" shall not in principle exclude the plurality of features and components described in this way.

Claim 1:
Hatch locking device (<NUM>) for an air- or spacecraft hatch (<NUM>), comprising:
a drivable spindle drive (<NUM>) which extends in a longitudinal axis (X) and is configured to be fixed in relation to a hatch frame (<NUM>) of the air- or spacecraft hatch (<NUM>) along the longitudinal axis (X);
at least one locking bolt (<NUM>) which is driven by the drivable spindle drive (<NUM>) and is guided along the longitudinal axis (X); and
at least one adjustment bush assembly (<NUM>) being mountable on a fuselage frame (<NUM>) and comprising a first eccentric bush (<NUM>) having a bolt receptacle (<NUM>) which is oriented centrally along the longitudinal axis (X) for receiving the at least one locking bolt (<NUM>) such that the hatch locking device (<NUM>) is positive-locking connectable in two axles (Y, Z) both being perpendicular to the longitudinal axis (X).