A component machining apparatus includes a measurement result acquiring unit and a machining data generator. The measurement result acquiring unit is configured to acquire a measurement result obtained by a measurer configured to measure a three-dimensional shape of a manufactured component among components of a structure. The manufactured component is manufactured earlier than a component of interest. The machining data generator is configured to generate machining data of the component of interest based on the measurement result of the manufactured component that has been acquired by the measurement result acquiring unit.

Systems and methods for measuring air gaps between opposing surfaces of two structural components. In one application, such measurements are used to fabricate a shim that fills the air gap between two structural members, such as parts of an aircraft. The resonant inductive coupling-based sensing system has the capability to remotely measure an air gap using an on-board transmit system. Furthermore, the system has the capability to switch between multiple inductor-capacitor sets such as to simultaneously measure air gaps across an area so that a better profile of the air gap can be determined. The resonant inductive coupling-based gap sensor is configured as signal generating and signal sensing electronics printed or mounted on respective flexible substrates to provide a flexible and portable measurement solution.

A component having a first part and a second part. The first part has a first interface surface and the second part has a second interface surface that is connected to the first interface surface via a bond. A digital profile of the first interface surface is used to shape the second interface surface to fit against the first interface surface with minimal to no gap therebetween before forming the bond. The digital profile is developed by scanning the first part with a scanner and the second part is shape by cutting or milling with a robotic arm that acts in accordance with a digital profile data read by a controller. The two parts are bonded via a weld that is automatically guided by the digital profile.

Systems and methods for measuring air gaps between opposing surfaces of two structural components. In one application, such measurements are used to fabricate a shim that fills the air gap between two structural members, such as parts of an aircraft. The resonant inductive coupling-based sensing system has the capability to remotely measure an air gap using an on-board transmit system. Furthermore, the system has the capability to switch between multiple inductor-capacitor sets such as to simultaneously measure air gaps across an area so that a better profile of the air gap can be determined. The resonant inductive coupling-based gap sensor is configured as signal generating and signal sensing electronics printed or mounted on respective flexible substrates to provide a flexible and portable measurement solution.

A component machining apparatus includes a measurement result acquiring unit and a machining data generator. The measurement result acquiring unit is configured to acquire a measurement result obtained by a measurer configured to measure a three-dimensional shape of a manufactured component among components of a structure. The manufactured component is manufactured earlier than a component of interest. The machining data generator is configured to generate machining data of the component of interest based on the measurement result of the manufactured component that has been acquired by the measurement result acquiring unit.

The present application discloses implementations relate to automated generation of interlocking joint features. An example method involves obtaining a virtual model of an object. The virtual model specifies dimensions of a first element, dimensions of a second element, and a spatial relation between the first element and the second element that defines a joint angle. The example method also involves obtaining a relationship that correlates element dimensions and joint angles with cut dimensions. The example method further involves determining cut dimensions for the first element the second element based on the relationship, the dimensions of the first element, the dimensions of the second element, and the joint angle. Modifying the first element and the second element according to the cut dimensions produces interlockable features on the first element and the second element. Additionally, the method involves providing an output signal indicative of the cut dimensions.

A device to correct geometrical differences of surfaces of parts to be assembled at the interface of the assembly. A measurer to acquire data by measuring the geometry of the assembly surfaces of two parts to be assembled to each other with their respective assembly surfaces facing. A simulator configured to simulate the assembly of the parts and to determine from the acquired data at each measured point of a sampling of the interface a thickness of the void resulting from the geometrical discrepancies between the assembly surfaces. An additive fabricator to receive from the simulator data representative of the thicknesses of the voids resulting from the geometrical discrepancies between the assembly surfaces. The additive fabricator configured to deposit material on the assembly surface of at least one of the parts to at least partly fill the void resulting from the geometrical discrepancies between the assembly surfaces.

A method of manufacturing an aircraft part for an assembly includes creating a 3D geometry model for an aircraft part having surface features and holes represented by the 3D geometry model and sized to nominal dimensions. The method includes generating a NC machining program directly from the 3D geometry model, with instructions for a single NC machining apparatus to machine the aircraft part, and including instructions to machine the holes to nominal. And the method includes machining the aircraft part utilizing the NC machining program. For this, the NC machining apparatus utilizes a hole-forming tool set at substantially the nominal, instead of at a high or low side of a related hole-diameter tolerance range to allow for tight geometric dimensioning and tolerancing requirements, whereby the holes are machined to substantially the nominal. This method enables the full process capability of the CNC machines while utilizing inspection tolerances that are measurable.

The invention relates to a method for producing bone treatment means, with a first step in which original 3D data of a bone or of a bone portion of a specific patient to be treated are made available, wherein a site to be treated is present inside the bone or the bone portion, with a second step involving the use of 3D data of a reference patient who has been selected according to predefined criteria, wherein the 3D data correspond to the bone or to the bone portion with the site to be treated, and with a third and reconstructive step for supplementing or completing 3D data for the reconstruction of the site to be treated, wherein a mirroring step is used in which 3D data of the specific patient to be treated, which have their origin on a mirror-symmetrical other side of the patient, are superposed, specifically at a site corresponding to the bone or bone portion, in order to obtain the combined 3D data.

A method of manufacturing an aircraft part for an assembly includes creating a 3D geometry model for an aircraft part having surface features and holes represented by the 3D geometry model and sized to nominal dimensions. The method includes generating a NC machining program directly from the 3D geometry model, with instructions for a single NC machining apparatus to machine the aircraft part, and including instructions to machine the holes to nominal. And the method includes machining the aircraft part utilizing the NC machining program. For this, the NC machining apparatus utilizes a hole-forming tool set at substantially the nominal, instead of at a high or low side of a related hole-diameter tolerance range to allow for tight geometric dimensioning and tolerancing requirements, whereby the holes are machined to substantially the nominal. This method enables the full process capability of the CNC machines while utilizing inspection tolerances that are measureable.