Aldo J Arena

US Patent:

7293920, Nov 13, 2007

Filed:

Mar 14, 2005

Appl. No.:

11/080164

Inventors:

Aldo Arena - Smithtown NY, US

Assignee:

Northrop Grumman Corporation - Los Angeles CA

International Classification:

F16C 19/49

US Classification:

384495

Abstract:

A self-aligning bearing assembly is disclosed which is capable of reacting both radial and axial loads. An inner bearing race is connected to a rotatable shaft that is subjected to such loads. An outer bearing race is installed within a housing and is capable of movement in multiple directions with respect to the housing. The outer bearing race can rotate in planes corresponding to longitudinal sections of the outer race, i. e. , rotational displacement. In addition, the outer bearing race can translate with respect to an inner wall of the housing in an axial direction of the housing, i. e. , axial displacement. Such movement is enabled by the use of radially displaceable thrust rings which contact the outer bearing race, and control of the geometry of the outer bearing race and inner wall of the housing.

US Patent:

53120701, May 17, 1994

Filed:

Apr 2, 1992

Appl. No.:

7/862318

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Grumman Aerospace Corporation - Bethpage NY

International Classification:

B64C 338

US Classification:

244 46

Abstract:

A segmented variable sweep wing for an aircraft has a plurality of wing segments. A structural device movably affixes the wing segments to the fuselage of the aircraft adjacent each other at their root areas. The structural device moves the segments conjointly to a power position where the segments are perpendicular to the fuselage and spaced from each other. The structural device also moves the segments conjointly to a cruise position wherein the segments are swept back at an angle with the fuselage and in abutment with each other thereby forming a unitary continuous surface airfoil.

US Patent:

56515138, Jul 29, 1997

Filed:

Mar 1, 1995

Appl. No.:

8/396843

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Northrop Grumman Corporation - Los Angeles CA

International Classification:

B64C 350

US Classification:

244 75R

Abstract:

A linear flap drive system for an aircraft having an airfoil and at least one flap which is extendable from the trailing edge of the fixed wing. More particularly the system includes linear drive elements and extending and positioning dynamic structures which together deploy the flaps from the airfoil. Further disclosed is a coupling of the dynamic structures to the corresponding flaps, by which coupling the process of extension causes an out-of-plane rotation of the flaps. In addition, there is provided a lateral end track and roller support assembly which guides the flaps as they are extended and positioned by the drive system. A lateral end power transmission assembly enables the linear drive assemblies to be driven by a common motive force.

US Patent:

58360700, Nov 17, 1998

Filed:

May 29, 1996

Appl. No.:

8/655063

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Northrop Grumman Corporation - Los Angeles CA

International Classification:

B21D 3900
B21D 2818

US Classification:

29523

Abstract:

A method for the fabricating or forming of tubular members of the torque tube type which may be utilized as torque joints for the drive shafts or steering connections of motor vehicles or in connection with articulating linkages for high-lift aircraft systems or for other various physical application where it is intended to react to torsional and axial loads which are ordinarily encountered in torque joints, steering linkages, drive shafts and the like. Provision is also made for a device which is in the form of a novel external die arrangement for electromagnetically concurrently forming longitudinal and circumferential or radial grooves in tubular members and interposed end fittings, particularly of the type which are adapted to react to torsional and axial loads encountered by torque joints and the like. For the concurrent formation of longitudinal and circumferential or radial grooves, the external die which encompasses the area of the components which is to be joined, has grooves or recesses machined in the circumferential inner surface of the die such that upon the generating of an electromagnetic force by means of an internal coil arranged within the area which is to be deformed, the superimposed tubular member and end fitting material is expanded outwardly so as to enter the recesses or grooves which are present in the inner encompassing surface of the external die. As a result, the interlocking groove structure or pattern formed in the tubular member and end fitting produces a torque joint which is adapted to react to both axial and torsional forces and loads imposed thereon.

US Patent:

45617996, Dec 31, 1985

Filed:

Sep 11, 1984

Appl. No.:

6/649284

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Grumman Aerospace Corp. - Bethpage NY

International Classification:

F16B 100

US Classification:

403285

Abstract:

A torque joint for transmission of force in both longitudinal and circumferential direction about thin-wall tubular torque tubes is provided by overlapping an inner one of said tubes and an outer one of said tubes, inserting a mandrel having longitudinal and circumferential slots therein, applying a deformation force for pressing the tubular members into the slots of the mandrels, and extracting at least a portion of the mandrel to provide the torque joint. In the case wherein two open-ended tubular members are employed, two mandrel elements of the same form are utilized, the two mandrel elements being withdrawn from the opposite ends of the joint upon completion of assembly of the joint. In the event that one of the tubular elements is closed ended, a retaining ring is utilized as one of the mandrel elements, in which case only one mandrel element is withdrawn while the ring remains captured between a circumferential groove of the joint and the closed end of the tube.

US Patent:

58550534, Jan 5, 1999

Filed:

Jun 18, 1996

Appl. No.:

8/664727

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Northrop Grumman Corporation - Los Angeles CA

International Classification:

B23P 1100
B21B 1702
B21D 2818

US Classification:

29523

Abstract:

A method which is directed to the fabricating or forming of tubular members of the torque tube type which may be utilized as torque joints for the drive shafts or steering connections of motor vehicles or in connection with articulating linkages for high-lift aircraft systems, marine systems or for other various military or non-military commercial physical application where it is intended to react to torsional and axial loads which are ordinarily encountered in torque joints, steering linkages, drive shafts and the like. More particularly, pursuant to a further aspect, provision is made for a device which is in the form of a novel die arrangement for electromagnetically forming spirally oriented grooves in tubular members and therewith interposed end fittings, particularly of the type which are adapted to react to intense torsional and axial loads encountered by torque joints and the like, and which are designed to appreciably reduce or even essentially eliminate stress concentrations so as to improve upon the fatigue life and, resultingly, extend the service life or durability of the torque tube assembly.

US Patent:

52519864, Oct 12, 1993

Filed:

Aug 10, 1992

Appl. No.:

7/926311

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Grumman Aerospace Corporation - Bethpage NY

International Classification:

F16C 3304

US Classification:

384272

Abstract:

A bushing assembly for use in eliminating axial and radial play in a connection joint is disclosed wherein the bushing assembly is comprised of various members which can be interconnected so that it can be assembled as a unit. Although various embodiments of the invention are disclosed, the bushing assembly of the present invention generally comprises first and second concentrically mounted sleeve members which are engaged along oppositely tapered surfaces such that the sleeve members, when axially tightened, are radially expanded. Both of the sleeve members are axially split so as to create a hoop stress which aids in eliminating the axial and radial play and which can increase the fatigue life of the connection joint.

US Patent:

50980432, Mar 24, 1992

Filed:

Feb 27, 1990

Appl. No.:

7/485541

Inventors:

Aldo Arena - Smithtown NY

Assignee:

Grumman Aerospace Corporation - Bethpage NY

International Classification:

B64C 902

US Classification:

244215

Abstract:

A rotary vane or geared rotary actuator housing is located within the interior space of a fixed aircraft wing section, forwardly of the rear spar. The actuator movable arm extends downwardly through the wing and articulates to a push rod which is pivotally connected to a movable control surface hinge fitting. A second fixed hinge fitting is connected to the rear spar, in the interior space of the fixed wing section. When the actuator operates, the arm is rotated thereby causing movement of the push rod and rotation of the control surface hinge fitting relative to the fixed hinge fitting. This results in deflection of the control surface. Location of the actuator housing forwardly of the rear spar and well forward of the hinge enables a designer to use larger and more powerful actuators since the forward end portion of the wing has greater interior volume than the hinge area. Control and power source lines are located within the wing section for protection. Further, control and power source components can be located in an area of the wing that allows integration of these components with the power hinge portion of the actuator into one line replaceable item.