Abstract: A torsional isolator (200, 300, 400) designed to reduce vibrations and shock experienced by electronics used during directional drilling is disclosed. The torsional isolator allows the drillstring electronics to oscillate at a slower rotational velocity than the data acquisition rate of associated sensors, such that the sensors record an average value of the azimuth heading thereby allowing for a higher accuracy measurement of the azimuth heading. The sample rate of the sensors is such that the sensors maximum error is reduced by the torsional isolator, as the output angular displacements are lower than the input angular displacements.

Abstract: A coupling suitable for transmitting torque applied to a first input to a second input shaft wherein the coupling accommodates angular changes between the input shafts. Additionally, the disclosure describes an improved mud motor transmission incorporating the coupling.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Abstract: A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Abstract: A device for absorbing vibration is disclosed, along with compensator elements for use therein. The device comprises a primary fluid system for dynamic isolation and/or damping, and a volume compensator having an auxiliary chamber fluidly interconnected with, but dynamically isolated from, the primary fluid system. The volume compensator features a compensator element having an elastic layer in fluid communication with the auxiliary chamber and disposed in sealing engagement within the device. The compensator element advantageously comprises a deformable elastomer stiffener cooperative with the elastic layer for providing static pressurization to the primary fluid system. The compensator element may further provide a reduced rate of change in volume stiffness characteristic that allows the fluid pressure in the primary fluid system to increase at a reduced rate. Further, the reduced rate characteristic prevents excessive static pressure swings. The compensator element may further comprise a seal bead.

Abstract: A Multi-Directional Tuned Vibration Absorber (MDTVA) (23) including a first tuning mass (32) vibrating at a first resonant frequency fn1 along a first axis, a second tuning mass (34) vibrating at the first resonant frequency along said first axis and also at a second resonant frequency fn2 along a second axis, a base member (21), a first spring (35) flexibly interconnected between the base member (21) and the first tuning mass (32), the first spring (35) substantially restricting motion of the first tuning mass (32) to motion along a first axis only, and a second spring (36) flexibly interconnected between the first tuning mass (32) and the second tuning mass (34), the second spring (36) substantially restricting relative motion between the first tuning mass (32) and second tuning mass (34), such that the relative motion of said second tuning mass (34) at said second frequency fn2 is along the second axis which is substantially perpendicular to the first axis.

Abstract: An active fluid mounting for isolating vibration between a vibrating member (21) and a structure (23). In one aspect, the active fluid mounting (20) includes an inner member (22), an outer member (24), a first flexible element (26), and an cartridge-like active fluid element (28) which is unitary and readily detachable, attached between the inner and outer members, (22) and (24).

Abstract: A method is described for identifying the primary load path of a particular engine. An elastomeric mount may then be made laterally soft in a first (in the disclosed case, the tangential) direction and more rigid in the direction of the primary load path. Efforts can then be directed to dynamically softening the mount in the primary load path. Specific apparatus may include passive fluid devices, active fluid devices, passive non-fluid devices and active non-fluid devices. In the case of a fluid mount, another feature of the invention is to have an auxiliary fill port of the volume compensator in alignment with at least one and, preferably both, of the primary fill port for the mount and the inertia track to facilitate filling.

Abstract: An isolation system (20) including the combination of an elastomeric mount (25) for attachment between a structure (24) and a vibrating member (22) and further including at least one passive tuned vibration absorber (TVA) (32) attached in the proximity the elastomeric mount (25) but on the structure side thereof. The resonant frequency f.sub.r of the passive TVA (32) is tuned to a resonant frequency f.sub.r just below the predominant operating frequency f.sub.o of the vibrating member (22), such that the resonance of the tuned vibration absorber (32) makes the structure (24) appear dynamically stiffer. In particular the ratio of f.sub.r /f.sub.o is in the range of between about 0.90 and 0.90. In one embodiment, the passive TVA (32) attaches directly to the inner member (28) of the elastomeric mount (25) and clamps the TVA assembly (43) to the structure (24) and clamps the structure (24) to the elastomeric mount (25).