Stabilized wing rib components and methods for assembling such stabilized wing rib components with at least one other aircraft airfoil structural component

Patent metadata

Field	Value
Publication number	US-10005565-B2
Application number	US-201414264209-A
Country	US
Kind code	B2
Filing date	Apr 29, 2014
Priority date	Apr 29, 2014
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

Devices and methods for stabilizing a structural component are provided. The devices may include a main body component, a pair of opposed stabilization feet engageable with opposed regions of the structural component, a pair of coaxially disposed and reciprocal rectilinearly movable support shafts coupling the stabilization feet to the main body component, and an actuator assembly for rectilinearly moving the support shafts opposite to one another which in turn moves the stabilization feet between retracted and extended positions relative to the main body component. In use, the device may be positioned between opposed flanges of a structural component so as to stabilize the component and facilitate automated assembly processes.

First claim

What is claimed is:

1. A stabilized wing rib component of an aircraft airfoil structure to facilitate automated drilling to permit assembly with at least one other airfoil structural component, wherein the stabilized wing rib component comprises:
a wing rib component which includes a central rib member having (i) opposed first and second rib surfaces, (ii) an opposed pair of lengthwise extending flanges which are upturned relative to the first rib surface, and (iii) a lengthwise oriented series of openings formed in the central rib member between the flanges which extending through the central rib member from the first rib surface to the opposed second rib surface, the flanges being adapted for connection with the at least one other airfoil structural component; and
a plurality of stabilization devices removably engaged with the wing rib component so as to stabilize the wing rib component during assembly with the at least one other airfoil structural component, wherein each of the stabilization devices includes:
(i) a main body component;
(ii) a pair of opposed stabilization feet which are elongated in a lengthwise direction of the wing rib component, wherein each of the stabilization feet includes an engagement surface at a terminal end thereof which is engaged with an inner region of a respective one of the opposed flanges of the wing rib component, wherein the stabilization feet include elongated open recessed channels being spaced apart from one another along a lengthwise direction of the stabilization feet and extending rearwardly from the engagement surface thereof to receive therein a drill bit during automated drilling of the opposed flanges to facilitate assembly of the wing rib component with the at least one other airfoil structure;
(iii) a pair of coaxially disposed and reciprocal rectilinearly opposed movable support shafts having distal ends coupled to a respective one of the stabilization feet so as to connect the stabilization feet to the main body component perpendicularly to the lengthwise direction of the wing rib component, and proximal ends having opposed beveled cam surfaces;
(iv) an actuator assembly comprising an actuator rod substantially perpendicular to the support shafts, the actuator rod being threadably coupled to the main body, wherein the actuator assembly comprises a terminal engagement end which operably interacts with the opposed beveled cam surfaces of the proximal ends of the support shafts for rectilinearly moving the support shafts opposite to one another in an actuation direction perpendicular to the enlongated direction of the stabilization feet, the support shafts being moved in the actuation direction in dependence upon turning movement of the actuator rod which in turn moves the stabilization feet between retracted and extended positions relative to the main body component so as to respectively disengage the stabilization feet from and engage the engagement surfaces of the stabilization feet with the inner regions of the opposed flanges;
(v) compression springs operatively associated with each of the support shafts for biasing the support shafts in a rectilinear inward direction relative to one another toward the retracted position thereof;
(vi) a base plate attached to the main body component, wherein the base plate includes an opposed pair of planar edges extending substantially parallel to the stabilization feet in the enlongated direction thereof and a pair of opposed arcuate edges at a terminal extent of the planar edges, the arcuate edges being configured to conformably mate to a respective one of the openings formed in the central rib member so that the base plate is positionally accepted within the respective one of the openings formed in the central rib member; and
(vii) a clamping assembly operatively connected to the base plate for positionally clamping the base plate within the respective one of the openings, wherein the clamping assembly comprises a clamp arm which is threadably coupled to the base plate, and clamp pads formed on opposed terminal ends of the clamp arm, the clamp arm being sufficiently elongated in the lengthwise direction of the wing rib component such that clamp arm spans the respective one of the openings of the central rib member and thereby position the clamp pads for releasable engagement with a subjacent region of the second rib surface of the central rib member adjacent to the respective one of the openings to thereby positionally fix the base plate within the respective one of the openings.

2. The device of claim 1 , wherein the main body component comprises an expansion chamber which houses the opposed proximal ends of the support shafts.

3. The device of claim 1 , wherein the actuator assembly comprises a handle connected to the actuator rod at an end opposite to the terminal engagement end thereof.

4. The device of claim 1 , wherein the clamp assembly includes a set screw for removably connecting the clamp arm to the base plate.

5. A method of fabricating an aircraft airfoil structure which comprises:
(a) providing the stabilized wing rib component according to claim 1 ;
(b) positioning the stabilized wing rib component adjacent to at least one other airfoil structural component to which the stabilized wing rib component is to be joined;
(c) drilling holes through the opposed flanges of the stabilized wing rib component and the at least one airfoil structural component to which the stabilized wing rib component is to be joined at locations corresponding to the elongated open recessed channels of the stabilization feet; and
(d) joining the stabilized wing rib component to the at least one airfoil component by inserting a fastener into the hole.

6. The method of claim 5 , wherein prior to step (a) the method further comprises clamping the plurality of stabilization devices to the wing rib component such that the opposed stabilization feet are engaged with respective inner regions of the opposed flanges thereof.

7. The method as in claim 6 , which prior to step (a) further comprises the steps of:
positioning the base plate of each stabilization device of the plurality of stabilization devices within a respective one of
the openings formed in the wing rib component; and

clamping the clamp arms which span the openings to the central rib member.

8. The method of claim 6 , which comprises operating each actuator assembly of each stabilization device of the plurality of stabilization devices so as to move the support shafts of each stabilization device in opposite outward directions relative to one another to thereby cause the stabilization feet to engage a respective one of the opposed flanges of the wing rib component.

9. The method of claim 5 which after step (d) further comprises the step of:
(e) removing the plurality of stabilization devices from the wing rib component.

10. The method of claim 9 , wherein step (e) comprises operating the actuator assembly of each stabilization device of the plurality of stabilization devices so as to move the engagement feet of the stabilization devices into the retracted position thereof, and disengaging the clamp feet from the opposed flanges of the central rib member.

Assignees

• Embraer Sa

Inventors

• De Oliveira Adir Rodrigues
• Endo Bianca Lis Rossi Dias
• Cruz Marcos Roberto
• De Miranda Pedro Candia
• Pinto Maurilio Augusto
• De Sousa Mauro Pereira

Classifications

• B23B47/284

  Jigs for drilling rivets or bolts · CPC title

• B23B2215/04

  Aircraft components · CPC title

• B23P2700/01

  Aircraft parts · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B23B47/287

  Jigs for drilling plate-like workpieces (templates for marking the position of fittings on wings or frames E05D11/0009) · CPC title