Warren E Schmidt DeceasedErie, PA

5176339, Jan 5, 1993

Sep 30, 1991

7/770058

Warren E. Schmidt - Erie PA

Lord Corporation - Erie PA

B64D 2700

244 54

A pivot type aircraft mounting for resiliently connecting a structure to an aircraft engine which uses a pivoting and siding joint on a beam at the engine attachment point, a vertically stiff and laterally soft intermediate pivot joint on the beam, and a resilient compression section near the end of the beam for reacting the engine loads into the structure and providing the desired spring rates in the vertical and lateral direction. The invention can utilize low friction pivoting and sliding joints such as nylon lines bearings or elastomeric bearings. The compression section can be metal mesh for high temperature applications or of elastomeric or laminated elastomeric construction for normal operating temperatures. The remote location of the compression section is particularly well suited for addition of fluid for adding damping or tuned absorber effects.

5906254, May 25, 1999

Feb 3, 1997

8/793029

Warren E. Schmidt - Erie PA
Douglas E. Ivers - Cary NC
Mark R. Jolly - Holly Springs NC
Mark A. Norris - Apex NC

Lord Corporation - Cary NC

F16F 710

188378

A flexibly-mounted active vibration absorber (AVA) which has a secondary controllable mass M. sub. 3. If the passive resonance of mass M. sub. 2 of the tuned absorber is insufficient to control the input vibration, a secondary mass M. sub. 3 is vibrated at a frequency, amplitude and phase sufficient to make up the deficiency in mass M. sub. 2. Many embodiments are described which depict variations on the first spring used for flexibly mounting the AVA, the actuators used to drive the AVA, and the attachment features for attaching to a vibrating member. Further in another aspect, means for counterbalancing the moments produced by the AVA are described.

4028002, Jun 7, 1977

Mar 1, 1976

5/662476

Robert H. Finney - Erie PA
Warren E. Schmidt - Erie PA

Lord Corporation - Erie PA

B64C 2738

416134A

A rotor blade retention system connects an elongated rotor blade to a rotor hub that is rotatable about its central axis. The connected rotor blade normally extends generally radially from the hub and is rotatable with the hub. The retention system includes at least three laminated elastomeric bearings connected together in serial compression load transmitting relationship. Each laminated bearing includes a plurality of alternating and bonded together layers of elastomeric material and substantially inextensible material. The layers of each of the serially interconnected bearings are at least partially inclined relative to the longitudinal axis of the rotor blade. In section taken radially of the longitudinal axis of the blade, at least a portion of each layer of each bearing projects longitudinally toward an end of the rotor blade. Preferably, only one of the serially interconnected bearings is rigidly connected to the rotor blade. The rotor blade is spaced radially, relative to its longitudinal axis, from at least all portions of the retention system other than the bearing to which the blade is rigidly connected.

4804352, Feb 14, 1989

Jan 30, 1987

7/009312

Warren E. Schmidt - Erie PA

Lord Corporation - Erie PA

B64C 2735
F16D 328
F16D 330

464 17

A link-type coupling particularly suited for use in connecting a drive shaft to a rotor hub in an aircraft for permitting the hub to rotate about an axis that may be angularly misaligned with respect to the rotational axis of the drive shaft. The coupling includes a series of links arranged tangentially with respect to the hub and shaft and connected thereto by laminated elastomeric bearings at the ends of the links. The laminated elastomeric bearings accommodate the motion of each link while transferring torque between the shaft and hub.

RE30262, Apr 29, 1980

Dec 26, 1978

6/000553

Warren E. Schmidt - Erie PA

Lord Corporation - Erie PA

B60G 1122

267152

A compressive load carrying laminated bearing comprising alternating bonded layers of a resilient material and a non-extensible material generally concentrically disposed about a common center with successive layers being disposed at successively increasing radii. The fatigue life thereof, when subjected to cylic rotational or torsional motion about the common center, is substantially enhanced by progressively increasing the thickness of the layers of resilient material with increasing radii while simultaneously progressively decreasing the modulus of elasticity of the layers of resilient material with increasing radii. . Iadd.

4821980, Apr 18, 1989

Sep 29, 1987

7/102045

Charles C. Clausen - Seattle WA
Ronald C. Johnson - Fall City WA
Wan T. Chee - Bellevue WA
Warren E. Schmidt - Erie PA

The Boeing Company - Seattle WA

B64D 2726

244 54

A strut for mounting an engine and isolating the vibration of the engine from the framework of an aircraft to which it is attached. An engine mounting strut (32) includes a forward spar (40), which extends outwardly from a rib (34) of an aircraft (20). An aft spar (62) similarly extends outward from a rib (38) and is pivotally connected to a box beam (42) in a vibration isolation mount (78). The pivotal axis of mount (78) is generally aligned with the longitudinal axis of the box beam. A vibration isolation arm (44) extends from a pivotal connection (82) having an axis generally orthogonal to the longitudinal axis of the box beam and is connected to the forward spar at two spaced-apart vibration isolation mounts (46 and 84). The spars are enclosed with an aerodynamic skin (56) forming a torque box 48, to which are attached forward and aft fairings (58).

5351930, Oct 4, 1994

Aug 11, 1992

7/928925

John J. Gwinn - Erie PA
Warren E. Schmidt - Erie PA
Marshall W. Downing - Chambourcy, FR

Lord Corporation - Erie PA

B64D 2726

248557

A mounting (20) which provides low vertical and lateral spring rates for excellent lateral and vertical vibration isolation yet provides a high roll stiffness for reacting torsional moments, while reducing isolator complexity and eliminating the need for a yoke or hanger. The mounting (20) includes a top member (34), a first arm (26) and a second arm (28) which are flexibly interleaved or attached. The first arm (26) is attached to a top member (34) by way of a pivot which can be a spring (30), the second arm (28) is also attached to the top member (34) by another pivot which can be a spring (32), and a third spring (36) attaches the arms (26) and (28) to each other. The arms (26) and (28) also attach to the supported member (22) preferably at their respective outboard ends (38), or at least one intermediate link can be used. The arms (26) and (28) are stiffly interconnected to one another, yet flexibly connected to a top member (34), such that relative vertical movement between the arms (26) and (28) is restricted. Thus a high roll stiffness is provided, yet allowing movement of the arms (26) and (28) as a unit for providing vertical and lateral isolation.

5108045, Apr 28, 1992

Apr 25, 1990

7/514071

Thomas R. Law - Edinboro PA
Warren E. Schmidt - Erie PA
Randall S. Wayland - Lake City PA

B64D 2726

241 54

A vibration isolating mount for connecting spaced structures and limiting noise transmission between the connected structures, such as between an aircraft and a turbine engine. The isolator comprises a pair of arms which are interconnected at one location by a torque tube pivotally connected to the aircraft structure and which are interconnected at another location by a tie brace which is also connected to the aircraft structure by a vibration isolator pad. The engine is connected to the arms by a hanger. The mount accepts various engine leads and reactions while minimizing the transmission of engine noise into the cabin of the aircraft.