Abstract: A system for visually pointing out locations on a three-dimensional structure such as an airframe of an aircraft includes a laser head that traverses an elongate track erected to pass through or adjacent to the structure. The laser head is traversed and stopped at various positions along the track, and from each position the laser head is calibrated by directing the laser beam onto three or more reference locations on the structure whose nominal coordinates are known in a reference coordinate system such as used in a CAD-CAM definition of the structure. The laser head is operable to determine in its own internal coordinate system the direction of the laser beam to each reference location and the distance to the reference location, and from this information a calibration is determined for relating measurements made by the laser head to the reference coordinate system.

Abstract: A system for visually pointing out locations on a three-dimensional structure such as an airframe of an aircraft includes a laser head that traverses an elongate track erected to pass through or adjacent to the structure. The laser head is traversed and stopped at various positions along the track, and from each position the laser head is calibrated by directing the laser beam onto three or more reference locations on the structure whose nominal coordinates are known in a reference coordinate system such as used in a CAD-CAM definition of the structure. The laser head is operable to determine in its own internal coordinate system the direction of the laser bean to each reference location and the distance to the reference location, and from this information a calibration is determined for relating measurements made by the laser head to the reference coordinate system.

Abstract: A method of forming a caul plate (14) for use in producing a composite honeycomb core sandwich panel (27). The uncured honeycomb core sandwich panel (27) is laid-up on a lay-up mandrel (20). An inner bagging film (28) is then extended over the uncured honeycomb core sandwich panel (27). Tooling prepreg sheets (34) are extended over the inner bagging film (28), and a outer bagging film (40) is extended over the tooling prepreg sheets (34). Reduced vacuum is applied to the inner bagging film (28), and full vacuum is applied to the outer bagging film (40). The tooling prepreg sheets (34) are then partially cured so that they harden into the shape of the inner mold line of the honeycomb core sandwich panel (27). The partially cured tooling prepreg sheets (34) are then final cured to form the caul plate (14). The caul plate (14) can then be used for inner mold line tooling for the honeycomb core sandwich panel (27) or parts having the same inner mold line shape.

Abstract: A method for fabricating a model includes the steps of stacking successive layers of aluminium honeycomb core to a desired height to form a block, machining the block to within a desired tolerance of the desired final contour, applying a layer of modeling material such as syntactic epoxy to the outer surface of the block, and machining the layer of modeling material to the desired contour. The result is a model from which a mold or composite parts can be fabricated, using high temperature and pressure processes if desired.

Abstract: A method for fabricating a model includes the steps of stacking successive layers of aluminum honeycomb core to a desired height to form a block, machining the block to within a desired tolerance of the desired final contour, applying a layer of modeling material such as syntactic epoxy to the outer surface of the block, and machining the layer of modeling material to the desired contour. The result is a model from which a mold or composite parts can be fabricated, using high temperature and pressure processes if desired.