Hatch locking device, air- or spacecraft hatch and air- or spacecraft

1 . A hatch locking device for a hatch for an aircraft or a space craft, the hatch locking device comprising:

a drivable spindle drive which extends in a longitudinal axis, is fixed in relation to a hatch frame of the hatch along the longitudinal axis and has an internal chamber oriented along the longitudinal axis;

a drive unit mounted to the hatch frame and configured to drive the drivable spindle drive;

two opposing locking bolts driven by the drivable spindle drive and guided along the longitudinal axis, wherein the two opposing locking bolts are within the internal chamber of the drivable spindle device and driven by the drivable spindle drive along the longitudinal axis such that a portion of the at least one locking bolt protrudes from the internal chamber; and

two adjustment bush assemblies each mounted on the fuselage frame mounted on a fuselage frame of the aircraft or the space craft and the adjustment bush assemblies comprise:

a first bush having a bolt receptacle oriented centrally along the longitudinal axis and configured to receive the portion of a first of the two opposing locking blots such that the hatch locking device is positive-locking connectable in two axes both perpendicular to the longitudinal axis.

2 . The hatch locking device according to claim 1 , wherein 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.

3 . The hatch locking device according to claim 1 , wherein each of the two opposing locking bolts includes an end region, and each of the end regions is encased in a bolt bush, wherein the bolt bush slides inside the drivable spindle drive to support the at least one locking bolt against a torque perpendicular to the longitudinal axis.

4 . The hatch locking device according to claim 1 , wherein the first of the two adjustment bush assemblies each comprises a second bush which partly surrounds an outer surface of the first bush,

wherein the first bush and the second bush each have a similar axle offset.

5 . The hatch locking device according to claim 4 , wherein the second bush has a conical shape and comprises teeth on a front side configured to rotate the second bush in relation to the first bush,

wherein the two adjustment bush assemblies further each comprise a nut interacting with the first bush and the nut is configured to press the second bush between the first bush and a fuselage frame.

6 . The hatch locking device according to claim 1 , wherein the two adjustment bush assemblies each further comprise a shim washer in a gap between the at least one locking bolt and the first bush along the longitudinal axis.

7 . The hatch locking device according to claim 1 , wherein the first bush is configured as a serrated, conical bush, and the first bush comprises teeth on a front side configured to suppress rotation of the first bush relative to the fuselage frame.

8 . A hatch assembly for an aircraft or a spacecraft hatch, the hatch assembly comprising:

a hatch frame for the aircraft or the spacecraft hatch;

a hatch locking device mounted to the hatch frame, the hatch locking device comprising:

a drivable spindle drive which extends in a longitudinal axis and is fixed in relation to the hatch frame along the longitudinal axis, wherein the drivable spindle device includes an internal chamber extending along the longitudinal axis;

at least one locking bolt within the internal chamber and driven by the drivable spindle drive along the longitudinal axis, wherein a portion of the at least one locking bolt extends from the internal chamber; and

at least one adjustment bush assembly is mounted on a fuselage frame of the aircraft or the space craft and the at least one adjustment brush comprises:

a first bush having a bolt receptacle oriented centrally along the longitudinal axis and is configured to receive the portion of the at least one locking bolt such that the hatch locking device is positive-locking connectable in two axes both perpendicular to the longitudinal axis;

a drive unit mounted to the hatch frame and configured to drive the drivable spindle drive, and

a pull-in device configured to force the hatch to close, wherein the pull-in device comprises a hollow cam disc mechanically coupled to the drive system and configured to interact with a pin mounted on a fuselage frame.

9 . The hatch assembly according to claim 8 , further comprising at least two of the hatch locking devices, wherein at least one of the hatch locking devices comprises two opposing locking bolts and wherein at least one hatch locking device comprises a locking bolt.

10 . The hatch assembly according to claim 8 , further comprising a drive system which mechanically couples the drive unit with the hatch locking device, wherein the drive system comprises at least one: a main drive shaft, a drive belt or a worm drive.

11 . The hatch assembly according to claim 8 , wherein the pull-in device further comprises a planetary gear arranged between the hollow cam disc and the drive system and configured to synchronize rotation of the hollow cam disc with rotation of the drivable spindle drive such that the hatch is at least almost closed before the bolt receptacle receives the locking bolt.

12 . An aircraft or a spacecraft including the hatch assembly according to claim 8 .

13 . The aircraft or the spacecraft of claim 12 , wherein the hatch assembly is configured as a cargo hold hatch.

14 . A hatch assembly for an aircraft or a spacecraft hatch, the hatch assembly comprising:

a first hatch frame and a second hatch frame parallel to the first hatch frame, wherein the first hatch frame includes a first aperture and the second hatch frame includes a second aperture aligned with the first aperture along a longitudinal axis;

a drivable spindle drive aligned with the longitudinal axis and fixed to the first hatch frame and to the second hatch frame;

a first locking bolt extending from a first end of the drivable spindle which drives the first locking bolt to move along the longitudinal axis relative to the first aperture of the first hatch frame;

a second locking bolt extending from a second end of the drivable spindle opposite to the first end, wherein the drivable spindle drives the second locking bolt to move along the longitudinal axis relative to the second aperture of the second hatch frame;

a first adjustment bush assembly mounted to a fuselage frame of the aircraft or the space craft, wherein the first adjustment brush includes a first bush including a first bolt receptacle aligned with the longitudinal axis and configured to receive the first locking bolt such that the hatch locking device is positive-locking connectable in two axes both perpendicular to the longitudinal axis;

a second adjustment bush assembly mounted to the fuselage frame, wherein the first adjustment brush includes a second bush including a second bolt receptacle aligned with the longitudinal axis and configured to receive the second locking bolt such that the hatch locking device is positive-locking connectable in the two axes both perpendicular to the longitudinal axis, and

a drive unit mounted to the hatch frame and configured to drive the drivable spindle drive to move the first locking bolt into and out of the first bolt receptacle and move the second locking bolt into and out of the second bolt receptacle.

15 . The hatch assembly of claim 14 , wherein the first adjustment bush assembly includes a further comprises a third bush which partly surrounds an outer surface of the first bush,

wherein the first bush and the third bush each have a similar axle offset.

16 . The hatch assembly according to claim 15 , wherein the third bush has a conical shape and comprises teeth on a front side configured to rotate the third bush relative to the first bush,

wherein the first adjustment bush assembly further comprises a nut interacting with the first bush and the nut is configured to press the third bush between the first bush and a fuselage frame.