Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.

Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.

Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.

Abstract: A creep forming tool modifies the shape of an aircraft component in the form of a wing skin portion. The tool includes a shaped surface defined by removable rib boards. The component is forced against the shaped surface, via a reusable intermediate plate. The shape of the shaped surface may be adjusted, if necessary, by replacing the rib boards with boards of a different shape.

Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.

Abstract: A method of creep forming a metallic component is provided. The method includes the steps of applying static loading and cyclic loading and/or vibration to the component during the creep forming thereof to act as a source of additional energy.

Abstract: A creep forming tool modifies the shape of an aircraft component in the form of a wing skin portion. The tool includes a shaped surface defined by removable rib boards. The component is forced against the shaped surface, via a reusable intermediate plate. The shape of the shaped surface may be adjusted, if necessary, by replacing the rib boards with boards of a different shape.

Abstract: A creep forming tool modifies the shape of an aircraft component in the form of a wing skin portion. The tool includes a shaped surface defined by removable rib boards. The component is forced against the shaped surface, via a reusable intermediate plate. The shape of the shaped surface may be adjusted, if necessary, by replacing the rib boards with boards of a different shape.

Abstract: A method of creep forming a metallic component is provided. The method includes the steps of applying static loading and cyclic loading and/or vibration to the component during the creep forming thereof to act as a source of additional energy.