QUICKLY ADJUSTABLE FAIL-SAFE LINK BAR ASSEMBLIES ESPECIALLY USEFUL FOR CONNECTING STRUCTURAL COMPONENTS OF AN AIRCRAFT

Abstract

Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.

Claims

1. A link bar assembly to connect adjacent structural components having connection lugs defining respective mounting openings, the link bar assembly comprising: a link bar having opposed terminal ends which include circular bearings; bushings operatively received by the circular bearings of the link bar; and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components, wherein at least one of the bushings includes a multi-faceted flange and defines an eccentric aperture such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.

2. The link bar assembly according to claim 1, further comprising at least one lock ring which includes an interior circular toothed surface for engagement with the multi-faceted flange of the at least one bushing.

3. The link bar assembly according to claim 2, wherein the at least one lock ring includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

4. The link bar assembly according to claim 1, which comprises an opposed pair of the bushings wherein each of the opposed pair of bushings includes a multi-faceted flange and defines an eccentric aperture.

5. The link bar assembly according to claim 4, further comprising a pair of lock rings each of which which includes the interior circular toothed surface for engagement with the multi-faceted flange of a respective on of the bushings.

6. The link bar assembly according to claim 5, wherein each of the lock rings includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug. The link bar assembly according to claim 1, wherein the eccentric aperture is elliptical aperture having major and minor axes.

8. The link bar assembly according to claim 1, wherein the bolt and pin assembly comprises a castle nut, and includes a threaded shank portion on the bolt of the bolt and pin assembly to threadably receive the castle nut.

9. The link bar assembly according to claim 1, wherein the link bar is axially elongate.

10. The link bar assembly according to claim 9, wherein the link bar has a cruciform cross-section.

11. An aircraft which comprises the link bar assembly according to claim 1.

12. An aircraft comprising separated adjacent structural components having respective connection lugs, and a link bar assembly connecting the separated structural components to one another, wherein the link bar assembly comprises: a link bar having opposed terminal ends which include circular bearings; bushings operatively received by the circular bearings of the link bar; and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to a respective one of the connection lugs of the adjacent structural components, wherein at least one of the bushings includes a multi-faceted flange and defines an eccentric aperture such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.

13. The aircraft according to claim 12, wherein the link bar assembly further comprises at least one lock ring which includes an interior circular toothed surface for engagement with the multi-faceted flange of the at least one bushing.

14. The aircraft according to claim 13, wherein the at least one lock ring includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

15. The aircraft according to claim 12, wherein the link bar assembly comprises an opposed pair of the bushings wherein each of the opposed pair of bushings includes a multi-faceted flange and defines an eccentric aperture.

16. The aircraft according to claim 15, further comprising a pair of lock rings each of which includes the interior circular toothed surface for engagement with the multi-faceted flange of a respective on of the bushings.

17. The aircraft according to claim 16, wherein each of the lock rings includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

18. The aircraft according to claim 12, wherein the eccentric aperture is elliptical aperture having major and minor axes.

19. The aircraft according to claim 12, wherein the bolt and pin assembly comprises a castle nut, and includes a threaded shank portion on the bolt of the bolt and pin assembly to threadably receive the castle nut.

20. The aircraft according to claim 12, wherein the link bar is axially elongate and has a cruciform cross-section.

Description

DETAILED DESCRIPTION OF EMBODIMENTS

[0017] Accompanying FIG. 1 depicts a link bar assembly 10 in accordance with the present invention installed between structural mounting flanges F1, W1 associated with aircraft structures associated with F and W structural components relative to the flight direction FD of an aircraft. As is depicted, the link bar assembly 10 is generally comprised of an axially elongate link bar 12 which in the embodiment depicted has a cruciform (+) cross-sectional shape which extends along an axis z transverse to the flight direction axis x. The link bar 12 includes upper and lower mounting assemblies 20, 40 at each terminal end 12a, 12b which serve to operatively connect the link bar 12 to the structural flanges F1 and W1 of the structures F and W, respectively.

[0018] The upper and lower mounting assemblies 20, 40 that operatively connect the link bar 12 to the upper and lower mounting flanges F1, W1, respectively, are depicted in greater detail in accompanying FIGS. 2 and 3. In this regard, it will be observed that each of the upper and lower mounting flanges F1, W1 include a spaced apart pair of connection lugs 22a, 22b and 42a, 44b which receive therebetween the terminal ends 12a, 12b, respectively, of the link bar 12. Each of the connection lugs 22a, 22b and 42a, 42b defines a circular opening that is respectively coaxially aligned with the circular bearing 24, 44 in the terminal ends 12a, 12b of the link bar 12.

[0019] As is perhaps better shown in FIG. 2, the upper mounting assembly 20 includes cylindrical bushing 26 received within the circular bearing 24 and which in turn receives an elongate threaded fail-safe bolt 28a and an elongate fail-safe hollow pin 28b sleeved over the bolt 28a. A castle nut 30 may thus be threaded over the terminal end of the bolt 28a so that a conventional cotter pin 32 can be inserted through the hole at the end of the bolt 28a. As is conventional, the individual legs of the cotter pin 32 can therefore be bent and engaged with the castle nut 30 so as to prevent the nut 30 from being back-threaded and thereby loosened during use. Suitable washers 34a, 34b may be positioned against the hex-head of the bolt 28a and the flange of the pin 28b.

[0020] In use, the lower mounting assembly 40 may be assembled following assembly of the upper mounting assembly 20 as described above to connect the terminal end 12a of the link bar 12 to the connection lugs 22a, 22b of the mounting flanges F1 associated with the structural component F. As is perhaps best shown in FIG. 3, the lower mounting assembly 40, like the upper mounting assembly 20, is similarly provided with an elongate fail-safe threaded bolt 48a, an elongate fail-safe hollow pin 48b sleeved over the shank of the bolt 48a, a castle nut 50 threaded over the terminal end of the bolt 48a, and a conventional cotter pin 52 inserted through the hole at the end of the bolt 48a and bent to prevent back-threading of the castle nut 50.

[0021] Important to the embodiment of the invention described herein, however, the lower mounting assembly 40 includes a pair of cylindrical adjustment bushings 54a, 54b each of which includes a multi-faceted adjustment flange 56a, 56b and a symmetrically non-circular aperture 58a, 58b. The apertures 58a, 58b are preferably elliptically shaped having major and minor axes. The adjustment bushings 54a, 54b are therefore positional in opposition to one another within the circular bearing 44 such that the multi-faceted adjustment heads 56a, 56b are positioned against a respective one of the connection lugs 42a, 42b. In the embodiment depicted, the adjustment heads have a hexagonal faceted configuration, but more or less facets may be provided as may be desired for the range of positional adjustment required.

[0022] During installation, the adjustment heads 56a, 56b may be rotated about the bushings 54a, 54b until the non-circular apertures thereof are sufficiently aligned with one another and the circular openings of the connection lugs 44a, 44b to allow the fail-safe bolt 48a to be inserted through such openings so that the pin 48b can be sleeved of the shank of the bolt 48a. Those in this art will appreciate that during installation and assembly, the non-circular openings of bushings 58a, 58a may not be sufficiently aligned with one another and the circular openings of the connection lugs 44a, 44b due to the non-circular apertures thereof. Thus, by selectively turning the adjustment flanges 56a and/or 56b, a greater area of the respective apertures can be presented until such time that the bolt 48a and pin 48b can be inserted through the circular openings of the connection lugs 44a, 44b and the non-circular apertures of the bushings 54a, 54b. Such adjustment will therefore cause the effective length L (see FIG. 1) of the link bar 12 to change somewhat so as to allow quick adjustment of the distance between the structural components F and W being connected together and thereby allow accommodation of assembly tolerances in the z axis.

[0023] Once the bushings 54a, 54b have been positioned to allow assembly of bolt 48a and pin 48b as described above, respective, lock rings 60a, 60b may be installed. As is shown in FIG. 3, each of the lock rings 60a, 60b includes an interior circular toothed surface 62a, 62b that allows virtually any number of positional dispositions relative to the multi-faceted flanges 58a, 58b of the bushings 54a, 54b, respectively, in dependence upon the number of teeth formed thereon. By way of example, the circular tooted surfaces 62a, 62b may be provided with 360 teeth to allow for a one degree positional change. Greater or lesser number of teeth may of course be provided. The toothed surfaces 62a, 62b may therefore be engaged with the multi-faceted flanges 58a, 58b so as to position the radially extending lobes 64a, 64b and present the locking apertures 66a, 66b formed in such lobes 64a, 64b in alignment with the receiving apertures 42a-1, 42b-1 of the flanges 42a, 42b, respectively. A threaded bolt 70 and nut 72 assembly with associated washers 74 may then be inserted through such aligned apertures, 66a, 66b and 42a-1, 42b-1 and threadably connected so as to positionally lock the lock rings 60a, 60b and thereby prevent rotational movement of the bushings 54a, 54b.

[0024] Those in this art will recognize that the embodiment disclosed herein above may be modified in several respects. For example, the link bar 12 may take any desired cross-sectional configuration and does necessarily need to be axially elongate, but could be angularly bent so that the terminal ends 12a, 12b are disposed at a relative angular position (e.g., up to about 90) relative to one another. Moreover, more than a single link bar 12 and its associated mounting assemblies may be provided. Additionally or alternatively, each of the terminal ends of the link bar 12 may be provided with adjustable bushings and lock rings and/or the adjustable bushings and lock rings may be provided on the upper mounting assembly rather than the lower mounting assembly as shown in the embodiment disclosed herein.

[0025] Therefore, while reference is made to a Once the particular embodiment of the invention, various modifications within the skill of those in the art may be envisioned. Therefore, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope thereof.