Line transfer system for airplane

• US 9,651,935 B2
• Filed: 02/12/2014
• Issued: 05/16/2017
• Est. Priority Date: 04/17/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Stone, Patrick B.
• Primary Examiner(s): Xavier, Valentina
• Application Number:
  US14/179,291
• Publication Number:
  US 20140163715A1
• Time in Patent Office: 1,189 Days
• CPC Class Codes: B23P 19/10 Aligning parts to be fitted together
• CPC Class Codes: B23P 2700/01 Aircraft parts
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor
• CPC Class Codes: G05B 19/402 characterised by control arrangements for positioning, e.g. centring a tool relative to a hole in the workpiece, additional detection means to correct position G05B19/19 takes precedence

Abstract

A method is provided for establishing a physical reference inside an airplane representing the airplane'"'"'s optimized line of flight based on the as-built orientation of aerodynamically significant features of the airplane. Values generated for aerodynamic pitch, roll and yaw representing the optimized line of flight are used to orient a tool reference surface outside the airplane. The orientation of the tool reference surface is recorded using an inertial reference unit placed on the tool reference surface. The tool reference surface and inertial reference unit are moved into the airplane where they are used to establish the physical reference on the airframe.

Claims

1. A system used to establish a physical reference within an airplane representing an optimized line of flight for the airplane, comprising:

a tool positioned outside the airplane and including a tool reference surface;

means for calculating values for aerodynamic pitch, roll, and yaw of the airplane representing the optimized line of flight;

means coupled with the calculating means for moving the tool reference surface to an orientation corresponding to the calculated values for aerodynamic pitch, roll, and yaw of the airplane representing the optimized line of flight; and

means for transferring the orientation of the tool reference surface to a location inside the airplane.

2. The system of claim 1, further comprising means for generating a data file representing an as-built orientation of at least one aerodynamically significant feature of the airplane, and wherein the calculating means uses the data file to calculate the values of aerodynamic pitch, roll, and yaw representing the optimized line of flight of the airplane.

3. The system of claim 1, wherein the means for moving the tool reference surface includes servo motors for moving the tool reference surface about pitch, roll, and yaw axes.

4. The system of claim 1, wherein the means for transferring the orientation of the tool reference surface includes means mounted on the tool reference surface for recording the orientation of the tool reference surface.

5. The system of claim 4, wherein:

the recording means includes an inertial reference unit, and

the tool reference surface is removably mounted on the tool to allow the tool reference surface and the inertial reference unit to be moved into the airplane.

6. A system for assembling and optimizing the line of flight of an airplane, comprising:

a jacking system including servos for moving components of the airplane into a final assembly position;

a tool including a movable tool reference surface;

means for calculating values for aerodynamic pitch, roll, and yaw of the airplane representing the optimized line of flight based on the position of the servos;

means coupled with the calculating means for moving the tool reference surface to an orientation corresponding to the calculated values for aerodynamic pitch, roll, and yaw of the airplane; and

means for transferring the orientation of the tool reference surface to a physical reference inside the airplane.

7. The system of claim 6, wherein the tool includes a tool base disposed outside the airplane, and the tool reference surface is removably mounted on the tool base.

8. The system of claim 6, wherein the means for transferring the orientation includes an inertial reference unit mounted on the tool reference surface.

9. The system of claim 6, wherein the tool reference surface includes guides for establishing the physical reference inside of the airplane.

10. The system of claim 6, wherein:

the calculating means includes a computer, and

the servo motors are controlled by the computer.

11. The system of claim 6, wherein the servo motors include:

at least three servo motors for controlling the pitch and the roll of the tool reference surface, and

a fourth servo motor for controlling the yaw of the tool reference surface.

12. The system of claim 6, wherein the means for transferring the orientation of the tool reference surface includes a yaw adjusting device carried on the tool reference surface for adjusting the yaw of the tool reference surface inside the airplane.

13. A system for assembling components of an airplane, including a physical reference on an airframe of the airplane representing an optimized line of flight for the airplane, comprising:

a jacking system including servos for moving components of the airplane into a final assembly position;

computer means for determining an as-built orientation of one or more aerodynamically significant features of the airplane based on the final position of the servos and for calculating the values pitch, roll, and yaw representing the optimized line of flight for the airplane using the as-built orientation;

a tool assembly located outside the airplane, including a tool base and a tool reference surface;

a fastener system for removably mounting the tool reference surface on the tool base;

servo motors controlled by the computer means for moving the tool reference surface to an orientation substantially matching the calculated values of pitch, roll and yaw; and

an inertial reference unit mounted on the tool reference surface for recording the orientation of the tool reference surface when the servo motors have moved the tool reference surface to the orientation substantially matching the calculated values of pitch, roll, and yaw, and for reorienting the tool reference surface on the airframe to match the recorded orientation.