Cutting by use of rotating axially moving tool – Processes – Bit detachable
Patent
1984-02-13
1986-07-08
Sipos, John
Cutting by use of rotating axially moving tool
Processes
Bit detachable
408 76, 408 98, 409178, 409180, B23B 3500, B23B 3914
Patent
active
045990182
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
Drilling a long series of holes to secure body panels and wing panels to substructures such as stringers, spar chords and other stiffeners in airframe manufacture is a common and repetitive operation. The spacing accuracy of such holes in load bearing structures is sufficiently critical to require templates to maintain hole spacing, pitch and end margin control. Further, countersinking is required to maintain flushness for fasteners protruding into the slip stream. In view of the large number of stringers, spar chords, and stiffeners employed in monocoque aircraft structures, there is an incentive to automate this common manufacturing task. Of particular interest is that of assemblying completed body panels and wing panels to their underlying skeletel structures where hand held drill motors are used for drilling and countersinking as two successive operations.
SUMMARY OF THE INVENTION
A pair of drilling units are each mounted for movement in an X and a Y direction to a frame or carriage. The carriage is mounted to a pair of support members, with each support member adjustable between extending pressure feet and extending rollers to contact a surface, and each support member having a latch mechanism to attach to and release from latch bolts mounted along the surface. The drilling units also each have a latch mechanism to attach to and release from the mounted latch bolts.
DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a perspective view of the traversing drilling unit of this invention in use.
FIGS. 2, 3 and 4 show a plan view, a side elevational view, and an end view of the traversing part of this invention.
FIG. 5 shows a cross sectional view taken along line 5--5 of FIG. 3.
FIG. 6 shows a blown up cross sectional view taken along line 6--6 of FIG. 3.
FIG. 7 shows a blown up fragmented view as in FIG. 6 with a drill latch of this invention superimposed.
FIG. 8 shows a cross sectional side elevational view of latch bolt placement to a surface to be drilled, for holding the traversing part of this invention.
FIGS. 9 through 13 show plan views illustrating steps in operating this invention.
FIG. 14 shows a block diagram of the controls for this invention.
DETAILED DESCRIPTION
A traversing drilling unit 10, has a control cabinet 12, a carriage 14 upon which is mounted a pair of drilling units 16, and a pair of support members 18, and an interconnecting control line 20.
This unit, is for mounting to and drilling holes along an elongated surface. It is especially useful in drilling various outside skin panels such as body panels and wing panels. The following description and illustrations relate to, but do not limit, its application to an airplane wing 22. An airplane wing as shown in FIG. 8 has a skin 24, lengthwise extending spars and or stringers shown as 26, and laterally extending ribs 28. A series of lock bolts 30 are aligned along the wing and are located at each rib. The lock bolt is preferably as shown with a bolt 32 having a head tapered on the inside at 34, a sleeve 36 formed on one end at 38 to allow insertion into a hole and to be expanded out by the tapered bolt head to lock the bolt in place, and a bobbin 40 with tripple flanges 42a, 42b and 42c. This lock bolt may be inserted, locked, unlocked and removed all from one side. The preferred lock bolt as described above, grips the stack of parts between two opposed compression faces so the compressive gripping forces are distributed over a large area. Other clamp up collets that expand within the hole will distort the hole through point loading. Such devices are not suitable for soft aluminum, composite or fiber reinforced plastic skin structures.
The carriage 14 is made up with a pair of spaced apart parallel H shaped members 44, joined together at each end with plates 46. Each of these members has a downward extending projection or rib 48 shaped to contact and to support a shaft 50 that extends along the length of the H shaped member. These shafts are aligned to be parallel to each other. A threaded bar 52 is locate
REFERENCES:
patent: 2871730 (1959-02-01), Gremp
patent: 3706505 (1972-12-01), Stoutguard
patent: 4268196 (1981-05-01), Harrow
Case M. A.
Donahue B. A.
Sipos John
The Boeing Company
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