Abstract: The present disclose describes a fluid isolator mount. The mount provides a long service life under high temperatures and large dynamic displacements. The mount utilizes metallic flexures and dynamic fluid chambers. The mount provides vibration isolation at selected frequencies while precluding damping effects.

Abstract: The present disclosure provides an improved circular force generator having a housing configured to reduce vibrational forces transmitted to an aircraft structure. Additionally, the disclosed configuration provide the necessary safety redundancies required by the aviation industry. The circular force generator includes mounting point around the exterior of the CFG housing and a central mounting point thereby providing redundant mounting points.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: Devices, systems, and methods for damping vibration of a structural component or power-transmission shafts are disclosed. Damping devices, systems, and methods utilize a lightweight damping device, which is targeted at reducing the resonant amplitude of the first several beaming modes and/or torsional modes of bending a structural component comprising a hollow shaft or strut. The damping device includes a stiff concentric tube with damping elements disposed at each end. The device is inserted within the original structural component or shaft and attached thereto. When the primary shaft undergoes bending due to modal characteristics, the damping elements react to dissipate energy, which effectively reduces the resonant amplitude.

Abstract: Engine mounting systems and methods that reduce engine core bending provide a first forward mount (130) connectable to a forward part of an engine core of an aircraft, an aft mount (150) connectable to an aft part of the core, and in a variant a second forward mount (140) connectable to the engine radially outward from the longitudinal axis of the engine with respect to the first forward mount, e.g. to a fan casing. The first forward mount reacts forces in a longitudinal, a lateral and a vertical direction. The aft mount reacts forces in the lateral direction and moments about the longitudinal direction, and in a variant vertical forces only from a predetermined pitch deflection of the engine. Stiffness values of the (first) forward and/or aft mount in the vertical direction may be reduced upon a fan blade off event.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.

Abstract: An engine attachment system (EAS) includes a forward collar (202), an aft collar (204), at least one truss subassembly (216) disposed between the forward collar and the aft collar for supporting an engine, and at least one vibration isolator (206,208) integrated with each of the forward and aft collars for isolating engine vibration and reducing noise. A method of attaching a turboprop engine includes providing an EAS and hoisting a turboprop engine at least partially within the at least one truss subassembly (216).

Abstract: Devices, systems, and methods for damping vibration of a structural component or power-transmission shafts are disclosed. Damping devices, systems, and methods utilize a lightweight damping device, which is targeted at reducing the resonant amplitude of the first several beaming modes and/or torsional modes of bending a structural component comprising a hollow shaft or strut. The damping device includes a stiff concentric tube with damping elements disposed at each end. The device is inserted within the original structural component or shaft and attached thereto. When the primary shaft undergoes bending due to modal characteristics, the damping elements react to dissipate energy, which effectively reduces the resonant amplitude.

Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.

Abstract: An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.

Abstract: An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.

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: An engine attachment system (EAS) includes a forward collar (202), an aft collar (204), at least one truss subassembly (216) disposed between the forward collar and the aft collar for supporting an engine, and at least one vibration isolator (206,208) integrated with each of the forward and aft collars for isolating engine vibration and reducing noise. A method of attaching a turboprop engine includes providing an EAS and hoisting a turboprop engine at least partially within the at least one truss subassembly (216).