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

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.

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.