BACKGROUND

[0001] This invention was made with government support under U.S. Army Contract

No. W58RGZ-08-C-0003. The government therefore has certain rights in this invention.

[0002] The present disclosure relates to a fitting assembly, and more particularly to a fitting assembly which facilitates installation of equipment through accommodation of airframe build and supplier component structure tolerances. [0003] A variety of equipment may be mounted within an aircraft cabin. Aircrew seats, litters and weapon racks, for example, may be mounted to the cabin floor with a fitting which permits the installation and removal of the equipment to reconfigure the aircraft as required.

[0004] Some equipment which is interchangeably mounted within the aircraft cabin may require a structurally tight installation which does not generate a mount preload. Such equipment may not readily accommodate airframe build and equipment tolerances. Assembly may thereby necessitate the mix-and-match of specific equipment to specific aircraft to complete each installation.

SUMMARY

[0005] An eccentric fitting assembly according to an exemplary aspect of the present disclosure includes an outer eccentric fitting which defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis. An inner eccentric fitting defines an inner axis, the inner eccentric fitting defines a stud receiver opening offset from the inner axis, the inner eccentric fitting receivable within the opening.

[0006] A method of mounting equipment to a stud according to an exemplary aspect of the present disclosure includes attaching an outer eccentric fitting to the equipment, the outer eccentric fitting defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis. Attaching an inner eccentric fitting such that a stud opening surrounds the stud, the inner eccentric fitting defines an inner axis, the stud opening offset from the inner axis. Receiving the inner eccentric fitting within the opening such that the inner eccentric fitting engages the stud and the inner eccentric fitting rotates within the opening to compensate for an offset between the equipment and the stud.

BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows:

[0008] Figure 1 is a schematic view of a rotary-wing aircraft embodiment for use with the present disclosure;

[0009] Figure 2A is a perspective view within a cabin of a rotary- wing aircraft with a munition launcher supported upon a stand removably mounted to a cabin floor; [0010] Figure 2B is a perspective view of a stud within the cabin floor;

[0011] Figure 3 is an exploded view of the eccentric fitting assembly;

[0012] Figure 4A is a schematic section view of the eccentric fitting assembly in a first position;

[0013] Figure 4B is a schematic line view of the eccentric fitting assembly in a second position; and

[0014] Figure 5 is a schematic sectional line view of a spring pin system of the eccentric fitting assembly.

DETAILED DESCRIPTION

[0015] Figure 1 schematically illustrates a rotary- wing aircraft 10 having a main rotor system 12. The aircraft 10 includes an airframe 14 having an extending tail 16 which mounts an anti-torque system 18. Although a particular helicopter configuration is described in the disclosed embodiment, other configurations and/or machines, such as high speed compound rotary-wing aircraft with supplemental translational thrust systems, dual contra-rotating, coaxial rotor system aircraft, turbo-props, tilt-rotors, tilt-wing and straight wing aircraft, will also benefit herefrom. The aircraft 10 may carry munitions 20 such as sonobuoys.

[0016] Referring to Figure 2 A, the munitons 20 may be contained within a launcher 22 supported upon a stand 24. The stand 24 may be removably mounted within the aircraft cabin. The stand 24 includes two pivot arms 26A, 26B which interface with two lower window mount fittings 28A, 28B and two stand support legs 30A, 3OB. Each of the stand interfaces are close tolerance fits for structural considerations and may not allow for normal tolerance variations in the airframe and stand even with the telescopic adjustment in the height of the stand support legs 30A, 30B (Figure 3). [0017] An eccentric fitting assembly 36 mountable to each of the legs 3OA, 30B facilitate interface with a respective stud 32 in the cabin floor 34 (Figure 2B). The eccentric fitting assembly 36 may be threaded into the legs 30A, 30B without interference with the telescopic adjustment. The eccentric fitting assembly 36 readily retrofits with other standard threaded/stud mount arrangements. It should be understood that although a sonobuoy stand is illustrated in the disclosed non-limiting embodiment, other equipment such as racks, crew seats and litters employed in military or commercial aircraft will also benefit from usage of the eccentric fitting assembly 36 disclosed herein.

[0018] Referring to Figure 3, the eccentric fitting assembly 36 generally includes an outer eccentric fitting 40, an inner eccentric fitting 42, an outer spring pin system 44, an inner spring pin system 46 and a lock ring 48. Relative rotation of the outer eccentric fitting 40 and the inner eccentric fitting 42 results in adjustment of the centerline of the eccentric fitting assembly 36. The outer eccentric fitting 40 and the inner eccentric fitting 42 are generally cylindrical in the illustrated non-limiting embodiment, but may alternatively be of a polygonal configuration to facilitate installation and adjustment with a tool. [0019] A threaded section 4OT of the outer eccentric fitting 40 facilitates installation of the eccentric fitting assembly 36 to the respective stand support legs 3OA, 30B or other equipment. It should be understood that attachments other than the threaded section 4OT may alternatively or additionally be provided.

[0020] The outer eccentric fitting 40 includes an opening 52 which is sized to receive the inner eccentric fitting 42. The opening 52 is offset from a longitudinal axis A defined by the outer eccentric fitting 40. The inner eccentric fitting 42 includes a stud opening 54 which is also offset from a longitudinal axis B defined by the inner eccentric fitting 42.

[0021] The offset of opening 52 and stud opening 54 is equivalent such that relative rotation of the outer eccentric fitting 40 and the inner eccentric fitting 42 positions the stud opening 54 from along axis A which can be adjusted to achieve the true center of the eccentric fitting assembly 36 (Figure 4A) to a maximum radial offset when the outer eccentric fitting 40 and the inner eccentric fitting 42 define a relative rotational position of 180 degrees (Figure 4B). Through the relative rotation of the outer eccentric fitting 40 and the inner eccentric fitting 42, an axis b of the stud opening 54 may be located anywhere within a diameter. [0022] Referring to Figure 4A, the outer spring pin system 44 is located within the outer eccentric fitting 40 transverse to axis A such that a multiple of lock pins 56 are receivable within a slot 58 defined about the outer perimeter of the inner eccentric fitting 42. Each of the lock pins 56 are biased outward relative axis A by a spring 60 and retained within the outer eccentric fitting 40 by a retainer 66 (Figure 5). The spring 60 reacts against a flange 68 formed by the lock pin 56. Alternatively, the flange 68 may be formed by a clip ring or the like attached to the lock pin 56.

[0023] The inner spring pin system 46 is located within the stud opening 54 transverse to axis B such that a multiple of stud lock pins 62 are engageable with the stud 32. Each of the stud lock pins 62 are biased outward relative axis B by a spring 64 and are mounted within the inner eccentric fitting 42 as discussed with regard to the outer spring pin system 44.

[0024] The eccentric fitting assembly 36 facilitates installation of the stand 24 or other equipment onto the cabin floor 34 or other surface with studs 32. The threaded section 4OT of the outer eccentric fitting 40 is threaded into the respective stand support legs 30A, 30B or other equipment. The inner eccentric fitting 42 is located over the stud 32. The outer eccentric fitting 40 is then located over the inner eccentric fitting 42 such that the inner eccentric fitting 42 is received within the opening 52. Insertion of the inner eccentric fitting 42 within the opening 52 drives the stud lock pins 62 into the stud opening 54 to lock the multiple of stud lock pins 62 onto the stud 32. The lock ring 48 is then mounted onto the outer eccentric fitting 40 to drive the multiple of lock pins 56 into the slot 58 to lock the inner eccentric fitting 42 within the outer eccentric fitting 40 to thereby lock the eccentric fitting assembly 36 together and attach the stand 24 to the cabin floor 34. The lock ring 48 may be engaged with the outer eccentric fitting 40 through a threaded or sliding engagement.

[0025] The eccentric fitting assembly 36 facilitates installation of equipment through accommodation of airframe build and supplier component structure tolerances yet reacts any upward or downward loads. Preservation of standard threaded stand and floor stud interfaces allow the eccentric fitting assembly 36 to be is directly retro fϊtable to legacy aircraft.

[0026] It should be understood that relative positional terms such as "forward," "aft," "upper," "lower," "above," "below," and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting. [0027] It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.

[0028] Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.

[0029] The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.