METHOD AND MACHINING EQUIPMENT FOR MACHINING AN AIRCRAFT STRUCTURAL COMPONENT

Claims

1. Method for machining an aircraft structural component (2) using a machining system (1), wherein the machining system (1) has a drilling unit (3a) and a riveting unit (3b), wherein a manufacturing process control (9) for activating the components of the machining system (1) is provided, wherein the manufacturing process control (9) executes a series of drilling procedures by means of the drilling unit (3a) and of riveting procedures by means of the riveting unit (3b) based on tool control data (9a) according to a manufacturing specification (10). wherein the manufacturing system (1) has an optical sensor (12) and a projection unit (13), wherein the method comprises the steps: - projecting a pattern (M), using the projection unit (13), onto a machining point (B) with a rivet element (4) inserted into a drilled hole (11) of the machining point (B), - detecting the machining point (B), including the projection of the pattern (M), using the sensor (12) and generating corresponding detection data (14) by means of the sensor (12), - analysing the detection data (14) by means of an analysis unit (15), - adapting the tool control data (9a) for a drilled hole (11) which is to be subsequently drilled according to the manufacturing specification (10) at a further machining point (B1), in particular the countersink depth (T) of the drilled hole (11) to be drilled, by means of the manufacturing process control (9) based on the analysis of the detection data (14).

2. Method according to Claim 1, characterized in that a head projection (K) of the rivet element (4) is determined during the analysis, and / or in that an angled position of the rivet element (4) is determined during the analysis, preferably in that, based on this analysis, the countersink depth (T) is adapted in the tool control data (9a) for the drilled hole (11) which is to be subsequently drilled.

3. Method according to Claim 1 or 2, characterized in that the pattern (M) comprises at least one stripe (16), preferably in that the pattern (M) is a striped projection having at least two or at least three, in particular parallel, stripes (16).

4. Method according to one of the preceding claims, characterized in that at least one stripe (16) is wider or narrower than the other stripe(s) (16) and / or a mutual distance between the stripes (16) differs.

5. Method according to one of the preceding claims, characterized in that the pattern (M) consists exclusively of parallel stripes (16) or in that the pattern (M) consists of a predetermined point cloud (17) or in that the pattern (M) is a grid pattern (18), preferably in that the grid pattern (18) consists of polygons, in particular triangles (18a) and / or squares (18b) .

6. Method according to one of the preceding claims, characterized in that, at the machining point (B), the head projection (K) is determined by identifying an offset (V) of the pattern (M), in particular of one or more stripes (16) of the pattern (M), on the head (4b) of the rivet element (4) in relation to the pattern (M) on the aircraft structural component (2) at the machining point (B) or with respect to a reference (R).

7. Method according to one of the preceding claims, characterized in that, at the machining point (B), an angled position of the rivet element (4) is determined by identifying a rotation (D) of the pattern (M) on the head (4b) of the rivet element (4) with respect to the pattern (M) on the aircraft structural component (2) at the machining point (B) or with respect to a reference (R) and / or by identifying a compression or elongation (S) of the pattern (M) on the head (4b) of the rivet element in relation to the pattern (M) on the aircraft structural component (2) at the machining point (B) or with respect to a reference (R).

8. Method according to one of the preceding claims, characterized in that, during the detection of the machining point (B), the projection unit (13) and the sensor (12) are directed onto this machining point at an angle (α) to one another, preferably in that this angle (α) is between 20° and 90°, further preferably between 45° and 75°, further preferably between 55° and 65°, and is in particular substantially 60°.

9. Method according to one of the preceding claims, characterized in that, during the detection, the projection unit (13) is directed onto the machining point (B) at an angle in relation to the longitudinal axis of the drilled hole (11), preferably in that the angle (β) between the direction of the projection (P) by the projection unit (13) and the longitudinal axis (11b) of the drilled hole (11) is between 45° and 75°, further preferably between 55° and 65°, and is in particular substantially 60°.

10. Method according to one of the preceding claims, characterized in that, during the detection, the sensor (12) is directed onto the machining point (B) from above, in particular orthogonally.

11. Method according to one of the preceding claims, characterized in that the analysis and the adaptation is based on detection data (14) which are generated when the rivet element (4) is inserted and the rivet connection is not yet produced, and / or in that the analysis and the adaptation is based on detection data (14) which are generated when the rivet element is inserted and the rivet connection is already produced.

12. Method according to one of the preceding claims, characterized in that a measuring device (19) for measuring the rivet elements (4) before their insertion into the drilled holes (11) is provided and in that the tool control data (9a) for the drilled hole (11) which is to be subsequently drilled according to the manufacturing specification (10) at the further machining point (B1) is additionally also adapted based on the measurement of the rivet element (4) which is to be positioned in this drilled hole (11).

13. Method according to one of the preceding claims, characterized in that the rivet element (4) inserted into the drilled hole (11) of the machining point (B) has also been measured by the measuring device (19) before its insertion and in that the tool control data (9a) for the drilled hole (11) which is to be subsequently drilled according to the manufacturing specification (10) at the further machining point (B1) are additionally also adapted based on the measurement of the rivet element (4) inserted into the drilled hole (11) of the machining point (B).

14. Method according to one of the preceding claims, characterized in that the method is repeated at the further machining point (B1) as a new machining point (B1) and the tool control data (9a) are adapted for a machining point (B2) following this new machining point (B1).

15. Method according to one of the preceding claims, characterized in that the manufacturing process control (9) detects whether the rivet element (4) which is to be positioned at the further machining point (B1) belongs to the same batch as the rivet element (4) inserted at the machining point (B) or whether it belongs to a new batch, preferably in that, if the rivet element (4) which is to be positioned at the further machining point (B1) belongs to a new batch, the method is repeated at the further machining point (B1) as a new machining point (B1) and the tool control data (9a) are adapted for a machining point (B2) following this new machining point (B1).

16. Machining system for machining an aircraft structural component (2), wherein the machining system (1) has a drilling unit (3a), a riveting unit (3b), a manufacturing process control (9) for activating the components of the machining system (1), an optical sensor (12) and a projection unit (13), wherein the machining system (1) for machining an aircraft structural component (2) is designed and configured according to the method according to one of Claims 1 to 15.