Diagnosis System

• US 20100268366A1
• Filed: 11/29/2007
• Published: 10/21/2010
• Est. Priority Date: 11/29/2007
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Kott, Horst
• Granted Patent: US 8,972,034 B2
• Time in Patent Office: Days
• US Class Current: 700/108
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

According to an exemplary embodiment of the present invention, a diagnosis system for detecting a state of emergency during assembly of a fuselage (101) of an airplane is provided, which is adapted for detecting an emergency event and outputting information relating to the actual position of the emergency event. This may provide for a fast error identification during airplane assembly.

Claims

1. Diagnosis system detecting a state of emergency during assembly of a fuselage of an airplane, the diagnosis system comprising:

a detection unit (200) for detecting a state of emergency when the fuselage (101) is in a first assembly state; and

an output unit (100) for outputting position information to a user when the state of emergency is detected;

wherein the position information relates to a local position at which the state of emergency is detected.

2. The diagnosis system of claim 1,

wherein the diagnosis system is adapted for preventing a movement of the fuselage (101) from the first position (301) to the second position (302) when the state of emergency is detected.

3. The diagnosis system of claim 1 or 2,

wherein the diagnosis system is adapted for preventing an assembling of the fuselage (101) from the first assembly state to a second assembly state when the state of emergency is detected.

4. The diagnosis system of one of the preceding claims,

wherein the state of emergency corresponds to a local difference between a target state and an actual state of the diagnosis system and the fuselage (101).

5. The diagnosis system of one of the preceding claims,

wherein the detection unit (200) comprises a detector (202);

wherein the detector (202) is adapted as one of an optical sensor, a pressure sensor, and a switch.

6. The diagnosis system of claim 5,

wherein the detector (202) comprises a photo sensor or a laser.

7. The diagnosis system of one of the preceding claims,

wherein the output unit (100) is adapted for indicating, to the user, the position at which the state of emergency is detected by marking the position on a graphical representation of the target state.

8. The diagnosis system of one of the preceding claims,

wherein the diagnosis system is adapted for moving a wing of an airplane from the first position (301) to the second position (302).

9. The diagnosis system of one of the preceding claims,

wherein outputting the position information and preventing the movement of the fuselage (101) from the first position (301) to the second position (302) is performed automatically.

10. A method for detecting a state of emergency during assembly of a fuselage of an airplane, the method comprising the steps of:

detecting a state of emergency when the fuselage (101) is in a first assembly state;

outputting position information to a user when the state of emergency is detected;

wherein the position information relates to a local position at which the state of emergency is detected.

11. The method of claim 10, further comprising the step of:

preventing a movement of the fuselage (101) from a first position (301) to a second position (302) when the state of emergency is detected.

12. The method of claim 10 or 11, further comprising the step of:

preventing an assembling of the fuselage (101) from the first assembly state to a second assembly state when the state of emergency is detected.

13. A computer-readable medium (402), in which a computer program for detecting a state of emergency during assembly of a fuselage of an airplane, is stored which, when being executed by a processor (401), causes the processor to carry out the steps of:

detecting a state of emergency when the fuselage (101) is in a first assembly state;

outputting position information to a user when the state of emergency is detected;

wherein the position information relates to a local position at which the state of emergency is detected.

14. A program element for detecting a state of emergency during assembly of a fuselage of an airplane, which, when being executed by a processor (401), causes the processor to carry out the steps of:

detecting a state of emergency when the fuselage (101) is in a first assembly state;

outputting position information to a user when the state of emergency is detected;

wherein the position information relates to a local position at which the state of emergency is detected.

15. A data processing unit for detecting a state of emergency during assembly of a fuselage of an airplane, the data processing unit comprising:

a memory for storing a target state of the fuselage;

a processor (401) adapted for;

detecting a state of emergency when the fuselage (101) is in a first assembly state;

outputting position information to a user when the state of emergency is detected;

wherein the position information relates to a local position at which the state of emergency is detected.