Integrated assembly system

• US 4,937,768 A
• Filed: 03/06/1989
• Issued: 06/26/1990
• Est. Priority Date: 04/14/1987
• Status: Expired due to Fees

• Current Assignee: Northrop Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Corporation (Northrop Grumman Corporation)
• Inventors: Zamzow, Charles E., Mladenoff, Donald D., Carver, Larry L.
• Primary Examiner(s): MACDONALD, ALLEN R
• Application Number:
  US07/319,604
• Time in Patent Office: 477 Days
• Field of Search: 364/188, 364/189, 364/191, 364/192, 364/474.22, 364/474.23, 364/474.24, 364/552, 364/425, 364/521, 364/522, 364/571.01
• US Class Current: 703/1
• CPC Class Codes: B29C 64/141 using only solid materials
• CPC Class Codes: G05B 19/4097 characterised by using design data to control NC machines, e.g. CAD/CAM G05B19/4093 takes precedence
• CPC Class Codes: G05B 19/41805 characterised by assembly
• CPC Class Codes: G05B 19/41865 characterised by job scheduling, process planning, material flow
• CPC Class Codes: G05B 2219/31407 Machining, work, process finish time estimation, calculation
• CPC Class Codes: G05B 2219/31415 Cost calculation in real time for a product manufactured
• CPC Class Codes: G05B 2219/35043 Tool, fixture design
• CPC Class Codes: G05B 2219/35095 Features library
• CPC Class Codes: G05B 2219/35194 From workpiece data derive tool data
• CPC Class Codes: G05B 2219/35196 From workpiece data derive assembly tool data
• CPC Class Codes: G05B 2219/35317 Display tool shape, to select tool for program, or for interference
• CPC Class Codes: G05B 2219/36352 Select tool as function of part shape, number of grooves and groove width
• CPC Class Codes: G05B 2219/37205 Compare measured, vision data with computer model, cad data
• CPC Class Codes: G06T 17/00 Three dimensional [3D] modelling, e.g. data description of 3D objects
• CPC Class Codes: Y02P 90/02 Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

Abstract

A method of assembling the separate components of a multi-component article includes generating a master definition of the article as a graphic data set in a 3-dimensional graphics computer system including coordinate points precisely locating the design definition in a three dimensional coordinate system. Data sub sets of the master definition are selected for component parts of the article including coordinate points. The data sub sets are transferred to a tool and component parts of the article are formed on the tool utilizing the data sub sets. The formed parts include physical markings thereon corresponding to the coordinate points of the master design definition. The data sub set are further downloaded to a microprocessor controlled measuring device. The measuring device is calibrated to the master design definition utilizing the physical markings on one of the parts. Further of the parts are then located with respect to other of the parts by utilizing their physical markings and referencing these marking back to the master design definition via the microprocessor controlled measuring device.

Claims

1. A method of assembling the separate components of a multi-component article which comprises:

generating a master design definition of said article as a graphics data set in a data base in a 3-dimensional graphics computer system, said master design definition including coordinate points precisely locating said master design definition in a three dimensional coordinate system;

selecting as component data sub sets portions of said master design definition graphics data set, said component data sub sets each including graphics data for a component part of said article, each of said data sub sets including graphics data for a portion of a surface of said component part of said product and coordinate points associated with said surface, said coordinate points including the absolute position of said part in said master design definition graphics data set;

transferring said component data sets to means for forming said component parts;

forming said component parts with said means for forming said component parts such that said component parts emulate said graphics description of said component parts in said master design definition graphics data set and further include physical markings on said parts corresponding to said coordinate points of said master design definition graphics data set;

selecting a microprocessor controlled measuring means for measuring the spatial relationships of points in a three dimensional space;

downloading said component data sub sets to said microprocessor controlled measuring means;

calibrating said microprocessor controlled measuring means to said coordinate points on said master design definition graphics data set by operating said microprocessor controlled measuring means and measuring the physical points on one of said component parts and comparing said physical points to their corresponding respective coordinate points in said master design definition graphics data set;

locating a further of said component parts with respect to said one of said component parts; and

operating said microprocessor controlled measuring means to measure said physical markings on said further of said parts and comparing said measured physical markings of said further part to their corresponding respective coordinate points in said master design definition graphics data set to precisely position said further of said parts with respect to said one of said parts.

2. The method of assembling the separate components of a multi-component article of claim 1 further including:

selecting a microprocessor controlled optical measuring device as said microprocessor controlled measuring means.

3. The method of assembling the separate components of a multi-component article of claim 2 further including:

selecting a microprocessor controlled theodolite system as said microprocessor controlled optical measuring device.

4. The method of assembling the separate components of a multi-component article of claim 1 including:

selecting said means for forming said component parts as a numerically controlled tool means for machining articles.

5. The method of assembling the separate components of a multi-component article of claim 4 further including:

selecting said numerically controlled tool means from one of a set of tools consisting of numerically controlled machine tools, numerically controlled laser cutters, numerically controlled robots, computer numerically controlled machine tools, computer numerically controlled laser cutters and computer numerically controlled robots.

6. The method of assembling the separate components of a multi-component article of claim 1 further including:

generating said further data set to include at least a portion of said component parts formed as virtual planes;

each of said virtual planes including a surface locus; and

each of said surface loci located in said portion of said surface of said respective component part.

7. The method of assembling the separate components of a multi-component article of claim 6 including:

selecting said multi-component article to include a plurality of profile boards and at least one connector board;

selecting said profile boards to include at least one profile edge;

locating said profile edge of each of said profile boards in a mold line surface which defines said image of said part;

selecting each of said profile boards to further include locator means for fixedly locating said profile board with respect to said connector board;

selecting said connector board to further include locator means for fixedly locating said connector board with respect to each of said profile boards; and

selecting said respective locator means to each include a locator edge on said respective profile boards and said respective connector board.

8. The method of assembling the separate components of a multi-component article of claim 1 including:

selecting said multi-component article as an aircraft and said component parts as sections of said aircraft.

9. The method of assembling the separate components of a multi-component article of claim 8 including:

selecting at least a portion of sections of said aircraft as composite parts formed of a first material in a matrix of a second material; and

forming said composite parts utilizing a forming and heat curing tool, said tool having a body, said body including a complimentary image of at least a portion of said composite part.