Grumman Aerospace Corporation

Northrop Grumman Systems Corporation

Other

United Technologies Corporation

Aldo Arena

Robert L Benoit

Raymond J Bruchez, Jr

Christopher J Horan

James T Dixon

Jim D Stewart

Wayne K Movick

George E Mount

Brian Robinson

Russell H Hagerman

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.

Self-aligning bearing assembly capable of reacting radial and axial loads

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.

Method and forming die for fabricating spiral groove torque tube

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.

Method and forming die for fabricating torque joints

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.

Linear flap drive system

A compensation device receives an inlet fluid flow and adjusts the pressure at an outlet so as to maintain a constant Reynolds number throughout the operating temperature range of the fluid. This is accomplished by a metering valve device in the nature of a fluted pin which becomes displaced in response to fluid temperature variations. This displacement varies the exposed cross-sectional area of a fluted end of the pin as it becomes seated to a greater or lesser extent in response to temperature variations. This results in corresponding changes in pressure between the inlet and outlet of the device while maintaining a constant Reynolds number. An additional embodiment includes an unfluted pin which becomes seated in a fluted bore located in a removable knurled knob. This allows one to insert various knurled knobs with fluted bores which have geometric configurations particularly adapted for particular fluids. Such a modular approach avoids the necessity of dismantling the device.

Variable resistance temperature compensator

A differential linear actuator is disclosed which minimizes the torque that must be reacted by an input, rotary drive sleeve member. The differential linear actuator includes an actuator housing within which the drive sleeve is rotatably mounted. An intermediate actuating member is concentrically mounted between the actuator housing and the drive sleeve and is connected to the drive sleeve through a spline connection such that rotation of the drive sleeve results in rotation of the intermediate actuator member. In addition, due to the spline connection and a rotary to linear connection assembly between the intermediate actuator member and the actuator housing, rotation of the intermediate actuator member results in axial displacement of the member relative to the actuator housing. An elongated output member is further connected to a remote end of the intermediate actuator member through a second rotary to linear connection assembly such that rotation of the intermediate actuator member also causes the output member to be axially shifted. The two rotary to linear connection assemblies are designed such that rotation of the drive sleeve in a given direction causes the intermediate actuator member and the output member to axially shift in opposite directions with the output member being axially displaced relative to the actuator housing a distance greater than the intermediate actuator member. In addition, a linear variable displacement transducer is adapted to be connected between the actuator housing and the output member to sense the position of the output member which can then be used to control the drive to the drive sleeve.

Differential linear actuator

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.

Segmented variable sweep wing aircraft

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.

Bushing assembly

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.

Integrated power hinge actuator

An axisymmetric thrust vectoring exhaust nozzle includes a plurality of divergent flaps (30) each supported at the upstream end by a universal joint (32) and at the downstream end by a load link (34) connected to a unison ring (36) positioned by actuators (45).

Thrust vectoring exhaust nozzle

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.

Torque joint

A torque tube employing end members interconnected by a tubular member. The end members are provided with a male extension having radially spaced, axially extending grooves, the number of grooves, outer diameter of the end member, groove width and groove length being in prescribed proportions and ratios. The ends of the tubular member are positioned over the male end member extensions and the tube walls are conformed to the end member and grooves electromagnetically so that the tube walls are recessed into the grooves.

Torsion resistant grooved joint

Method of fabricating a torque joint

A wrench is formed of two jaws which are shaped to conform to standard fasteners, such as hex nuts, and are supported within a housing for translation relative to each other for gripping the fastener. Closing force on the jaws is exerted by a pivoting handle acting through an overcenter linkage. A crank-shaped lever is positioned contiguous to the overcenter linkage permits operation of the wrench with the jaws being either tightly clenched or slightly withdrawn from the fastener. One end of the overcenter linkage is connected to the housing by a screw which is rotated to set a spacing between the jaws.

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Smithtown, NY, United States of America

Aldo Arena